From dbe21090e83099af30a829e47e66b77c8bbc44e1 Mon Sep 17 00:00:00 2001 From: Matthew Clarke Date: Thu, 18 Nov 2021 01:08:55 -0800 Subject: [PATCH 1/2] Addition of control surface deflection --- .../body_axis_derivatives_case_01_01.txt | 62 +-- .../body_axis_derivatives_case_01_02.txt | 62 +-- .../body_axis_derivatives_case_01_03.txt | 62 +-- .../body_axis_derivatives_case_01_04.txt | 62 +-- .../body_axis_derivatives_case_01_05.txt | 62 +-- .../body_axis_derivatives_case_01_06.txt | 62 +-- .../body_axis_derivatives_case_02_01.txt | 62 +-- .../body_axis_derivatives_case_02_02.txt | 62 +-- .../body_axis_derivatives_case_02_03.txt | 62 +-- .../body_axis_derivatives_case_02_04.txt | 62 +-- .../body_axis_derivatives_case_02_05.txt | 62 +-- .../body_axis_derivatives_case_02_06.txt | 62 +-- .../body_axis_derivatives_case_03_01.txt | 60 +-- .../body_axis_derivatives_case_03_02.txt | 62 +-- .../body_axis_derivatives_case_03_03.txt | 62 +-- .../body_axis_derivatives_case_03_04.txt | 62 +-- .../body_axis_derivatives_case_03_05.txt | 62 +-- .../body_axis_derivatives_case_03_06.txt | 62 +-- .../body_axis_derivatives_case_04_01.txt | 60 +-- .../body_axis_derivatives_case_04_02.txt | 62 +-- .../body_axis_derivatives_case_04_03.txt | 62 +-- .../body_axis_derivatives_case_04_04.txt | 62 +-- .../body_axis_derivatives_case_04_05.txt | 62 +-- .../body_axis_derivatives_case_04_06.txt | 62 +-- .../body_axis_derivatives_case_05_01.txt | 60 +-- .../body_axis_derivatives_case_05_02.txt | 62 +-- .../body_axis_derivatives_case_05_03.txt | 62 +-- .../body_axis_derivatives_case_05_04.txt | 62 +-- .../body_axis_derivatives_case_05_05.txt | 62 +-- .../body_axis_derivatives_case_05_06.txt | 64 +-- .../body_axis_derivatives_case_06_01.txt | 62 +-- .../body_axis_derivatives_case_06_02.txt | 62 +-- .../body_axis_derivatives_case_06_03.txt | 62 +-- .../body_axis_derivatives_case_06_04.txt | 62 +-- .../body_axis_derivatives_case_06_05.txt | 62 +-- .../body_axis_derivatives_case_06_06.txt | 62 +-- .../scripts/AVL/avl_files/commands_01.deck | 72 ++++ .../scripts/AVL/avl_files/commands_02.deck | 72 ++++ .../scripts/AVL/avl_files/commands_03.deck | 72 ++++ .../scripts/AVL/avl_files/commands_04.deck | 72 ++++ .../scripts/AVL/avl_files/commands_05.deck | 72 ++++ .../scripts/AVL/avl_files/commands_06.deck | 72 ++++ .../stability_axis_derivatives_case_01_01.txt | 68 +-- .../stability_axis_derivatives_case_01_02.txt | 68 +-- .../stability_axis_derivatives_case_01_03.txt | 68 +-- .../stability_axis_derivatives_case_01_04.txt | 68 +-- .../stability_axis_derivatives_case_01_05.txt | 68 +-- .../stability_axis_derivatives_case_01_06.txt | 68 +-- .../stability_axis_derivatives_case_02_01.txt | 68 +-- .../stability_axis_derivatives_case_02_02.txt | 68 +-- .../stability_axis_derivatives_case_02_03.txt | 68 +-- .../stability_axis_derivatives_case_02_04.txt | 68 +-- .../stability_axis_derivatives_case_02_05.txt | 68 +-- .../stability_axis_derivatives_case_02_06.txt | 68 +-- .../stability_axis_derivatives_case_03_01.txt | 62 +-- .../stability_axis_derivatives_case_03_02.txt | 66 +-- .../stability_axis_derivatives_case_03_03.txt | 68 +-- .../stability_axis_derivatives_case_03_04.txt | 68 +-- .../stability_axis_derivatives_case_03_05.txt | 68 +-- .../stability_axis_derivatives_case_03_06.txt | 68 +-- .../stability_axis_derivatives_case_04_01.txt | 62 +-- .../stability_axis_derivatives_case_04_02.txt | 68 +-- .../stability_axis_derivatives_case_04_03.txt | 68 +-- .../stability_axis_derivatives_case_04_04.txt | 68 +-- .../stability_axis_derivatives_case_04_05.txt | 68 +-- .../stability_axis_derivatives_case_04_06.txt | 68 +-- .../stability_axis_derivatives_case_05_01.txt | 62 +-- .../stability_axis_derivatives_case_05_02.txt | 68 +-- .../stability_axis_derivatives_case_05_03.txt | 68 +-- .../stability_axis_derivatives_case_05_04.txt | 68 +-- .../stability_axis_derivatives_case_05_05.txt | 68 +-- .../stability_axis_derivatives_case_05_06.txt | 74 ++-- .../stability_axis_derivatives_case_06_01.txt | 68 +-- .../stability_axis_derivatives_case_06_02.txt | 68 +-- .../stability_axis_derivatives_case_06_03.txt | 68 +-- .../stability_axis_derivatives_case_06_04.txt | 68 +-- .../stability_axis_derivatives_case_06_05.txt | 68 +-- .../stability_axis_derivatives_case_06_06.txt | 68 +-- .../AVL/avl_files/strip_forces_case_01_01.txt | 386 ++++++++--------- .../AVL/avl_files/strip_forces_case_01_02.txt | 400 ++++++++--------- .../AVL/avl_files/strip_forces_case_01_03.txt | 394 ++++++++--------- .../AVL/avl_files/strip_forces_case_01_04.txt | 384 ++++++++--------- .../AVL/avl_files/strip_forces_case_01_05.txt | 388 ++++++++--------- .../AVL/avl_files/strip_forces_case_01_06.txt | 390 ++++++++--------- .../AVL/avl_files/strip_forces_case_02_01.txt | 386 ++++++++--------- .../AVL/avl_files/strip_forces_case_02_02.txt | 392 ++++++++--------- .../AVL/avl_files/strip_forces_case_02_03.txt | 384 ++++++++--------- .../AVL/avl_files/strip_forces_case_02_04.txt | 390 ++++++++--------- .../AVL/avl_files/strip_forces_case_02_05.txt | 400 ++++++++--------- .../AVL/avl_files/strip_forces_case_02_06.txt | 390 ++++++++--------- .../AVL/avl_files/strip_forces_case_03_01.txt | 392 ++++++++--------- .../AVL/avl_files/strip_forces_case_03_02.txt | 402 +++++++++--------- .../AVL/avl_files/strip_forces_case_03_03.txt | 386 ++++++++--------- .../AVL/avl_files/strip_forces_case_03_04.txt | 394 ++++++++--------- .../AVL/avl_files/strip_forces_case_03_05.txt | 386 ++++++++--------- .../AVL/avl_files/strip_forces_case_03_06.txt | 394 ++++++++--------- .../AVL/avl_files/strip_forces_case_04_01.txt | 394 ++++++++--------- .../AVL/avl_files/strip_forces_case_04_02.txt | 394 ++++++++--------- .../AVL/avl_files/strip_forces_case_04_03.txt | 386 ++++++++--------- .../AVL/avl_files/strip_forces_case_04_04.txt | 388 ++++++++--------- .../AVL/avl_files/strip_forces_case_04_05.txt | 390 ++++++++--------- .../AVL/avl_files/strip_forces_case_04_06.txt | 392 ++++++++--------- .../AVL/avl_files/strip_forces_case_05_01.txt | 390 ++++++++--------- .../AVL/avl_files/strip_forces_case_05_02.txt | 398 ++++++++--------- .../AVL/avl_files/strip_forces_case_05_03.txt | 392 ++++++++--------- .../AVL/avl_files/strip_forces_case_05_04.txt | 390 ++++++++--------- .../AVL/avl_files/strip_forces_case_05_05.txt | 388 ++++++++--------- .../AVL/avl_files/strip_forces_case_05_06.txt | 388 ++++++++--------- .../AVL/avl_files/strip_forces_case_06_01.txt | 386 ++++++++--------- .../AVL/avl_files/strip_forces_case_06_02.txt | 400 ++++++++--------- .../AVL/avl_files/strip_forces_case_06_03.txt | 396 ++++++++--------- .../AVL/avl_files/strip_forces_case_06_04.txt | 388 ++++++++--------- .../AVL/avl_files/strip_forces_case_06_05.txt | 386 ++++++++--------- .../AVL/avl_files/strip_forces_case_06_06.txt | 382 ++++++++--------- .../avl_files/surface_forces_case_01_01.txt | 20 +- .../avl_files/surface_forces_case_01_02.txt | 26 +- .../avl_files/surface_forces_case_01_03.txt | 22 +- .../avl_files/surface_forces_case_01_04.txt | 20 +- .../avl_files/surface_forces_case_01_05.txt | 22 +- .../avl_files/surface_forces_case_01_06.txt | 24 +- .../avl_files/surface_forces_case_02_01.txt | 20 +- .../avl_files/surface_forces_case_02_02.txt | 22 +- .../avl_files/surface_forces_case_02_03.txt | 18 +- .../avl_files/surface_forces_case_02_04.txt | 22 +- .../avl_files/surface_forces_case_02_05.txt | 24 +- .../avl_files/surface_forces_case_02_06.txt | 20 +- .../avl_files/surface_forces_case_03_01.txt | 24 +- .../avl_files/surface_forces_case_03_02.txt | 28 +- .../avl_files/surface_forces_case_03_03.txt | 18 +- .../avl_files/surface_forces_case_03_04.txt | 24 +- .../avl_files/surface_forces_case_03_05.txt | 20 +- .../avl_files/surface_forces_case_03_06.txt | 20 +- .../avl_files/surface_forces_case_04_01.txt | 28 +- .../avl_files/surface_forces_case_04_02.txt | 24 +- .../avl_files/surface_forces_case_04_03.txt | 20 +- .../avl_files/surface_forces_case_04_04.txt | 24 +- .../avl_files/surface_forces_case_04_05.txt | 22 +- .../avl_files/surface_forces_case_04_06.txt | 20 +- .../avl_files/surface_forces_case_05_01.txt | 20 +- .../avl_files/surface_forces_case_05_02.txt | 22 +- .../avl_files/surface_forces_case_05_03.txt | 24 +- .../avl_files/surface_forces_case_05_04.txt | 20 +- .../avl_files/surface_forces_case_05_05.txt | 22 +- .../avl_files/surface_forces_case_05_06.txt | 20 +- .../avl_files/surface_forces_case_06_01.txt | 18 +- .../avl_files/surface_forces_case_06_02.txt | 26 +- .../avl_files/surface_forces_case_06_03.txt | 22 +- .../avl_files/surface_forces_case_06_04.txt | 22 +- .../avl_files/surface_forces_case_06_05.txt | 22 +- .../avl_files/surface_forces_case_06_06.txt | 20 +- regression/scripts/AVL/cruise_aero_data.txt | 72 ++-- .../scripts/AVL/cruise_stability_data.txt | 72 ++-- regression/scripts/AVL/test_AVL.py | 6 +- .../Analyses/Aerodynamics/AVL_Inviscid.py | 4 +- trunk/SUAVE/Analyses/Stability/AVL.py | 4 +- .../Aerodynamics/AVL/write_input_deck.py | 21 +- .../Aerodynamics/AVL/write_run_cases.py | 56 +-- 157 files changed, 10314 insertions(+), 9871 deletions(-) diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_01.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_01.txt index eebc2389d4..c4dfb235ef 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_01.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_01.txt @@ -13,54 +13,54 @@ Run case: case_01_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00049 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.25003 - CZtot = 0.04804 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = -0.04803 - CDtot = 0.00119 - CDvis = 0.00000 CDind = 0.0011874 - CLff = -0.04796 CDff = 0.0008417 | Trefftz - CYff = 0.00000 e = 0.0922 | Plane + CXtot = 0.00047 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.25074 + CZtot = 0.04717 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = -0.04716 + CDtot = 0.00118 + CDvis = 0.00000 CDind = 0.00118 + CLff = -0.04708 CDff = 0.00086 | Trefftz + CYff = 0.00000 e = 0.0873 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.006897 CXv = -0.000000 CXw = -0.225567 - y force CY | CYu = 0.000000 CYv = -0.813809 CYw = -0.000001 - z force CZ | CZu = -0.101932 CZv = -0.000001 CZw = -5.672218 - x mom. Cl | Clu = -0.000000 Clv = -0.173774 Clw = -0.000004 - y mom. Cm | Cmu = 0.222183 Cmv = -0.000001 Cmw = -7.966332 - z mom. Cn | Cnu = -0.000000 Cnv = 0.278184 Cnw = 0.000000 + x force CX | CXu = -0.006879 CXv = -0.000000 CXw = -0.223754 + y force CY | CYu = 0.000000 CYv = -0.813886 CYw = -0.000000 + z force CZ | CZu = -0.103691 CZv = -0.000000 CZw = -5.672500 + x mom. Cl | Clu = -0.000000 Clv = -0.173946 Clw = -0.000001 + y mom. Cm | Cmu = 0.223552 Cmv = -0.000000 Cmw = -7.967508 + z mom. Cn | Cnu = -0.000000 Cnv = 0.278218 Cnw = 0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = -0.000000 CXq = -1.186104 CXr = 0.000000 - y force CY | CYp = -0.309538 CYq = -0.000008 CYr = 0.977207 - z force CZ | CZp = -0.000009 CZq = -27.108837 CZr = 0.000001 - x mom. Cl | Clp = -0.484662 Clq = -0.000023 Clr = 0.165280 - y mom. Cm | Cmp = -0.000016 Cmq = -77.724060 Cmr = 0.000001 - z mom. Cn | Cnp = 0.138563 Cnq = 0.000004 Cnr = -0.513345 + x force CX | CXp = -0.000000 CXq = -1.188567 CXr = 0.000000 + y force CY | CYp = -0.309325 CYq = -0.000001 CYr = 0.977330 + z force CZ | CZp = -0.000001 CZq = -27.113642 CZr = 0.000000 + x mom. Cl | Clp = -0.484673 Clq = -0.000003 Clr = 0.165341 + y mom. Cm | Cmp = -0.000002 Cmq = -77.741516 Cmr = 0.000000 + z mom. Cn | Cnp = 0.138501 Cnq = 0.000001 Cnr = -0.513391 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = 0.000066 CXd2 = -0.000418 CXd3 = -0.000000 CXd4 = -0.000173 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000359 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000583 CZd2 = -0.025135 CZd3 = 0.000000 CZd4 = -0.012031 + x force CX | CXd1 = 0.000056 CXd2 = -0.000432 CXd3 = 0.000000 CXd4 = -0.000175 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000361 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000583 CZd2 = -0.025135 CZd3 = 0.000000 CZd4 = -0.012033 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001927 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000088 Cmd2 = -0.023284 Cmd3 = 0.000000 Cmd4 = -0.058272 - z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000072 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000089 Cmd2 = -0.023281 Cmd3 = 0.000000 Cmd4 = -0.058282 + z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000075 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_02.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_02.txt index 53f5a1c97b..a8e1b1d2da 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_02.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_02.txt @@ -13,54 +13,54 @@ Run case: case_01_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = -0.00210 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.02877 - CZtot = -0.15023 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.15023 - CDtot = 0.00210 - CDvis = 0.00000 CDind = 0.0020971 - CLff = 0.15019 CDff = 0.0014556 | Trefftz - CYff = 0.00000 e = 0.5229 | Plane + CXtot = -0.00202 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.02810 + CZtot = -0.15111 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.15111 + CDtot = 0.00202 + CDvis = 0.00000 CDind = 0.00202 + CLff = 0.15108 CDff = 0.00149 | Trefftz + CYff = 0.00000 e = 0.5181 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.004194 CXv = -0.000000 CXw = 0.077528 - y force CY | CYu = 0.000000 CYv = -0.819873 CYw = -0.000000 - z force CZ | CZu = -0.300457 CZv = -0.000001 CZw = -5.683236 - x mom. Cl | Clu = -0.000000 Clv = -0.197950 Clw = -0.000004 - y mom. Cm | Cmu = -0.057538 Cmv = -0.000002 Cmw = -8.014050 - z mom. Cn | Cnu = -0.000000 Cnv = 0.276472 Cnw = -0.000000 + x force CX | CXu = -0.004047 CXv = -0.000000 CXw = 0.081202 + y force CY | CYu = -0.000000 CYv = -0.819924 CYw = -0.000000 + z force CZ | CZu = -0.302224 CZv = -0.000000 CZw = -5.683418 + x mom. Cl | Clu = -0.000000 Clv = -0.198123 Clw = -0.000001 + y mom. Cm | Cmu = -0.056198 Cmv = -0.000000 Cmw = -8.014884 + z mom. Cn | Cnu = -0.000000 Cnv = 0.276504 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = -0.196756 CXr = 0.000000 - y force CY | CYp = -0.239545 CYq = -0.000007 CYr = 0.991879 - z force CZ | CZp = -0.000009 CZq = -27.145086 CZr = 0.000001 - x mom. Cl | Clp = -0.484302 Clq = -0.000023 Clr = 0.195371 - y mom. Cm | Cmp = -0.000016 Cmq = -78.041107 Cmr = 0.000002 - z mom. Cn | Cnp = 0.094390 Cnq = 0.000003 Cnr = -0.516802 + x force CX | CXp = 0.000000 CXq = -0.195168 CXr = 0.000000 + y force CY | CYp = -0.239303 CYq = -0.000001 CYr = 0.991999 + z force CZ | CZp = -0.000001 CZq = -27.149084 CZr = 0.000000 + x mom. Cl | Clp = -0.484317 Clq = -0.000003 Clr = 0.195433 + y mom. Cm | Cmp = -0.000002 Cmq = -78.053085 Cmr = 0.000000 + z mom. Cn | Cnp = 0.094324 Cnq = 0.000000 Cnr = -0.516846 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000193 CXd2 = -0.000034 CXd3 = 0.000000 CXd4 = -0.000068 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000335 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000596 CZd2 = -0.025113 CZd3 = 0.000000 CZd4 = -0.012032 + x force CX | CXd1 = -0.000204 CXd2 = -0.000045 CXd3 = 0.000000 CXd4 = -0.000069 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000338 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000596 CZd2 = -0.025113 CZd3 = 0.000000 CZd4 = -0.012034 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001924 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000110 Cmd2 = -0.023241 Cmd3 = 0.000000 Cmd4 = -0.058332 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000110 Cmd2 = -0.023240 Cmd3 = 0.000000 Cmd4 = -0.058340 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000041 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_03.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_03.txt index fd3083497e..c889b79db3 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_03.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_03.txt @@ -13,54 +13,54 @@ Run case: case_01_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00590 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.30900 - CZtot = -0.34840 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.34839 - CDtot = 0.00626 - CDvis = 0.00000 CDind = 0.0062649 - CLff = 0.34816 CDff = 0.0052006 | Trefftz - CYff = 0.00000 e = 0.7865 | Plane + CXtot = 0.00613 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.30835 + CZtot = -0.34929 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.34929 + CDtot = 0.00606 + CDvis = 0.00000 CDind = 0.00606 + CLff = 0.34905 CDff = 0.00525 | Trefftz + CYff = 0.00000 e = 0.7834 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.001486 CXv = -0.000000 CXw = 0.380527 - y force CY | CYu = -0.000000 CYv = -0.824938 CYw = 0.000000 - z force CZ | CZu = -0.498616 CZv = -0.000002 CZw = -5.687328 - x mom. Cl | Clu = -0.000000 Clv = -0.221884 Clw = -0.000004 - y mom. Cm | Cmu = -0.337190 Cmv = -0.000002 Cmw = -8.052002 - z mom. Cn | Cnu = -0.000000 Cnv = 0.274423 Cnw = -0.000000 + x force CX | CXu = -0.001211 CXv = -0.000000 CXw = 0.386059 + y force CY | CYu = -0.000000 CYv = -0.824962 CYw = -0.000000 + z force CZ | CZu = -0.500388 CZv = -0.000000 CZw = -5.687412 + x mom. Cl | Clu = -0.000000 Clv = -0.222059 Clw = -0.000001 + y mom. Cm | Cmu = -0.335879 Cmv = -0.000000 Cmw = -8.052497 + z mom. Cn | Cnu = -0.000000 Cnv = 0.274454 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = 0.792832 CXr = 0.000000 - y force CY | CYp = -0.169261 CYq = -0.000006 CYr = 1.005343 - z force CZ | CZp = -0.000008 CZq = -27.148266 CZr = 0.000002 - x mom. Cl | Clp = -0.483353 Clq = -0.000023 Clr = 0.225224 - y mom. Cm | Cmp = -0.000016 Cmq = -78.263054 Cmr = 0.000003 - z mom. Cn | Cnp = 0.050102 Cnq = 0.000003 Cnr = -0.519628 + x force CX | CXp = 0.000000 CXq = 0.798468 CXr = 0.000000 + y force CY | CYp = -0.168990 CYq = -0.000000 CYr = 1.005460 + z force CZ | CZp = -0.000001 CZq = -27.151451 CZr = 0.000000 + x mom. Cl | Clp = -0.483371 Clq = -0.000003 Clr = 0.225286 + y mom. Cm | Cmp = -0.000002 Cmq = -78.269577 Cmr = 0.000001 + z mom. Cn | Cnp = 0.050032 Cnq = 0.000000 Cnr = -0.519672 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000453 CXd2 = 0.000348 CXd3 = 0.000000 CXd4 = 0.000038 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000311 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000608 CZd2 = -0.025029 CZd3 = 0.000000 CZd4 = -0.012004 + x force CX | CXd1 = -0.000464 CXd2 = 0.000340 CXd3 = 0.000000 CXd4 = 0.000037 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000314 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000607 CZd2 = -0.025030 CZd3 = 0.000000 CZd4 = -0.012005 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001916 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000131 Cmd2 = -0.023143 Cmd3 = 0.000000 Cmd4 = -0.058250 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000131 Cmd2 = -0.023142 Cmd3 = 0.000000 Cmd4 = -0.058256 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000007 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_04.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_04.txt index ac7aef6da1..43c0d959d0 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_04.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_04.txt @@ -13,54 +13,54 @@ Run case: case_01_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.03763 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.72902 - CZtot = -0.64335 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.64418 - CDtot = 0.01858 - CDvis = 0.00000 CDind = 0.0185847 - CLff = 0.64424 CDff = 0.0166451 | Trefftz - CYff = -0.00000 e = 0.8414 | Plane + CXtot = 0.03822 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -0.72840 + CZtot = -0.64423 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.64511 + CDtot = 0.01807 + CDvis = 0.00000 CDind = 0.01807 + CLff = 0.64513 CDff = 0.01672 | Trefftz + CYff = -0.00000 e = 0.8401 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.002579 CXv = -0.000000 CXw = 0.834044 - y force CY | CYu = -0.000000 CYv = -0.830650 CYw = 0.000001 - z force CZ | CZu = -0.794641 CZv = -0.000002 CZw = -5.680476 - x mom. Cl | Clu = -0.000001 Clv = -0.257270 Clw = -0.000004 - y mom. Cm | Cmu = -0.755790 Cmv = -0.000003 Cmw = -8.090524 - z mom. Cn | Cnu = -0.000000 Cnv = 0.270724 Cnw = -0.000001 + x force CX | CXu = 0.003045 CXv = 0.000000 CXw = 0.842346 + y force CY | CYu = -0.000000 CYv = -0.830633 CYw = 0.000000 + z force CZ | CZu = -0.796416 CZv = -0.000000 CZw = -5.680411 + x mom. Cl | Clu = -0.000000 Clv = -0.257446 Clw = -0.000001 + y mom. Cm | Cmu = -0.754527 Cmv = -0.000001 Cmw = -8.090510 + z mom. Cn | Cnu = -0.000000 Cnv = 0.270751 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 2.275026 CXr = 0.000000 - y force CY | CYp = -0.063474 CYq = -0.000006 CYr = 1.023238 - z force CZ | CZp = -0.000008 CZq = -27.091022 CZr = 0.000002 - x mom. Cl | Clp = -0.480824 Clq = -0.000023 Clr = 0.269478 - y mom. Cm | Cmp = -0.000016 Cmq = -78.417145 Cmr = 0.000005 - z mom. Cn | Cnp = -0.016426 Cnq = 0.000002 Cnr = -0.522681 + x force CX | CXp = 0.000000 CXq = 2.286721 CXr = 0.000000 + y force CY | CYp = -0.063161 CYq = -0.000001 CYr = 1.023350 + z force CZ | CZp = -0.000001 CZq = -27.092983 CZr = 0.000000 + x mom. Cl | Clp = -0.480848 Clq = -0.000003 Clr = 0.269540 + y mom. Cm | Cmp = -0.000002 Cmq = -78.415459 Cmr = 0.000001 + z mom. Cn | Cnp = -0.016504 Cnq = 0.000000 Cnr = -0.522722 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000843 CXd2 = 0.000914 CXd3 = 0.000000 CXd4 = 0.000195 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000273 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000623 CZd2 = -0.024790 CZd3 = 0.000000 CZd4 = -0.011907 + x force CX | CXd1 = -0.000855 CXd2 = 0.000911 CXd3 = 0.000000 CXd4 = 0.000194 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000276 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000621 CZd2 = -0.024791 CZd3 = 0.000000 CZd4 = -0.011908 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001895 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000162 Cmd2 = -0.022890 Cmd3 = 0.000000 Cmd4 = -0.057861 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000162 Cmd2 = -0.022890 Cmd3 = 0.000000 Cmd4 = -0.057863 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000044 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_05.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_05.txt index 255ce2b514..222eacea87 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_05.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_05.txt @@ -13,54 +13,54 @@ Run case: case_01_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.07180 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.00684 - CZtot = -0.83705 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.83957 - CDtot = 0.03075 - CDvis = 0.00000 CDind = 0.0307508 - CLff = 0.84069 CDff = 0.0281052 | Trefftz - CYff = -0.00000 e = 0.8485 | Plane + CXtot = 0.07271 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -1.00621 + CZtot = -0.83793 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.84054 + CDtot = 0.02995 + CDvis = 0.00000 CDind = 0.02995 + CLff = 0.84158 CDff = 0.02819 | Trefftz + CYff = -0.00000 e = 0.8477 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.005285 CXv = -0.000000 CXw = 1.135194 - y force CY | CYu = -0.000000 CYv = -0.833194 CYw = 0.000001 - z force CZ | CZu = -0.990830 CZv = -0.000002 CZw = -5.667255 - x mom. Cl | Clu = -0.000001 Clv = -0.280475 Clw = -0.000004 - y mom. Cm | Cmu = -1.033776 Cmv = -0.000003 Cmw = -8.103891 - z mom. Cn | Cnu = -0.000000 Cnv = 0.267844 Cnw = -0.000001 + x force CX | CXu = 0.005879 CXv = 0.000000 CXw = 1.145332 + y force CY | CYu = -0.000000 CYv = -0.833150 CYw = 0.000000 + z force CZ | CZu = -0.992606 CZv = -0.000000 CZw = -5.667090 + x mom. Cl | Clu = -0.000000 Clv = -0.280651 Clw = -0.000001 + y mom. Cm | Cmu = -1.032548 Cmv = -0.000000 Cmw = -8.103537 + z mom. Cn | Cnu = -0.000000 Cnv = 0.267870 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 3.259943 CXr = 0.000000 - y force CY | CYp = 0.007165 CYq = -0.000005 CYr = 1.033612 - z force CZ | CZp = -0.000008 CZq = -27.011591 CZr = 0.000003 - x mom. Cl | Clp = -0.478406 Clq = -0.000023 Clr = 0.298577 - y mom. Cm | Cmp = -0.000015 Cmq = -78.400467 Cmr = 0.000006 - z mom. Cn | Cnp = -0.060765 Cnq = 0.000001 Cnr = -0.523920 + x force CX | CXp = 0.000000 CXq = 3.275660 CXr = 0.000000 + y force CY | CYp = 0.007506 CYq = -0.000001 CYr = 1.033721 + z force CZ | CZp = -0.000001 CZq = -27.012730 CZr = 0.000000 + x mom. Cl | Clp = -0.478433 Clq = -0.000003 Clr = 0.298640 + y mom. Cm | Cmp = -0.000002 Cmq = -78.393318 Cmr = 0.000001 + z mom. Cn | Cnp = -0.060847 Cnq = 0.000000 Cnr = -0.523960 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001101 CXd2 = 0.001284 CXd3 = 0.000000 CXd4 = 0.000297 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000248 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000631 CZd2 = -0.024555 CZd3 = 0.000000 CZd4 = -0.011807 + x force CX | CXd1 = -0.001114 CXd2 = 0.001285 CXd3 = 0.000000 CXd4 = 0.000297 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000250 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000629 CZd2 = -0.024557 CZd3 = 0.000000 CZd4 = -0.011807 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001875 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000182 Cmd2 = -0.022653 Cmd3 = 0.000000 Cmd4 = -0.057426 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000081 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000182 Cmd2 = -0.022654 Cmd3 = 0.000000 Cmd4 = -0.057426 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000078 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_06.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_06.txt index 1f91577fcd..80e6a971aa 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_06.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_01_06.txt @@ -13,54 +13,54 @@ Run case: case_01_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.14214 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.41689 - CZtot = -1.12085 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.12851 - CDtot = 0.05465 - CDvis = 0.00000 CDind = 0.0546506 - CLff = 1.13338 CDff = 0.0509013 | Trefftz - CYff = -0.00000 e = 0.8516 | Plane + CXtot = 0.14365 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -1.41624 + CZtot = -1.12170 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 1.12960 + CDtot = 0.05332 + CDvis = 0.00000 CDind = 0.05332 + CLff = 1.13427 CDff = 0.05101 | Trefftz + CYff = -0.00000 e = 0.8510 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.009332 CXv = -0.000000 CXw = 1.584212 - y force CY | CYu = -0.000000 CYv = -0.835105 CYw = 0.000001 - z force CZ | CZu = -1.282776 CZv = -0.000002 CZw = -5.634485 - x mom. Cl | Clu = -0.000001 Clv = -0.314633 Clw = -0.000004 - y mom. Cm | Cmu = -1.448289 Cmv = -0.000003 Cmw = -8.105426 - z mom. Cn | Cnu = -0.000000 Cnv = 0.262915 Cnw = -0.000001 + x force CX | CXu = 0.010115 CXv = 0.000000 CXw = 1.597080 + y force CY | CYu = -0.000000 CYv = -0.835022 CYw = 0.000000 + z force CZ | CZu = -1.284548 CZv = -0.000000 CZw = -5.634171 + x mom. Cl | Clu = -0.000000 Clv = -0.314809 Clw = -0.000001 + y mom. Cm | Cmu = -1.447114 Cmv = -0.000000 Cmw = -8.104561 + z mom. Cn | Cnu = -0.000000 Cnv = 0.262938 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000002 CXq = 4.729496 CXr = 0.000000 - y force CY | CYp = 0.113080 CYq = -0.000003 CYr = 1.046809 - z force CZ | CZp = -0.000008 CZq = -26.830782 CZr = 0.000003 - x mom. Cl | Clp = -0.473687 Clq = -0.000023 Clr = 0.341534 - y mom. Cm | Cmp = -0.000015 Cmq = -78.196381 Cmr = 0.000007 - z mom. Cn | Cnp = -0.127118 Cnq = -0.000000 Cnr = -0.524581 + x force CX | CXp = 0.000000 CXq = 4.751208 CXr = 0.000000 + y force CY | CYp = 0.113462 CYq = -0.000000 CYr = 1.046912 + z force CZ | CZp = -0.000001 CZq = -26.830685 CZr = 0.000000 + x mom. Cl | Clp = -0.473719 Clq = -0.000003 Clr = 0.341597 + y mom. Cm | Cmp = -0.000002 Cmq = -78.181023 Cmr = 0.000001 + z mom. Cn | Cnp = -0.127206 Cnq = -0.000000 Cnr = -0.524620 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001482 CXd2 = 0.001824 CXd3 = 0.000000 CXd4 = 0.000447 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000209 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000641 CZd2 = -0.024095 CZd3 = 0.000000 CZd4 = -0.011603 + x force CX | CXd1 = -0.001496 CXd2 = 0.001829 CXd3 = 0.000000 CXd4 = 0.000448 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000212 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000637 CZd2 = -0.024097 CZd3 = 0.000000 CZd4 = -0.011603 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001838 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000212 Cmd2 = -0.022196 Cmd3 = 0.000000 Cmd4 = -0.056516 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000130 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000211 Cmd2 = -0.022198 Cmd3 = 0.000000 Cmd4 = -0.056512 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000127 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_01.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_01.txt index 749a37a1a5..2029db6a35 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_01.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_01.txt @@ -13,54 +13,54 @@ Run case: case_02_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00049 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.25163 - CZtot = 0.04827 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = -0.04825 - CDtot = 0.00119 - CDvis = 0.00000 CDind = 0.0011936 - CLff = -0.04819 CDff = 0.0008482 | Trefftz - CYff = 0.00000 e = 0.0924 | Plane + CXtot = 0.00046 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.25235 + CZtot = 0.04739 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = -0.04738 + CDtot = 0.00120 + CDvis = 0.00000 CDind = 0.00120 + CLff = -0.04730 CDff = 0.00086 | Trefftz + CYff = 0.00000 e = 0.0875 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.006934 CXv = -0.000000 CXw = -0.226712 - y force CY | CYu = 0.000000 CYv = -0.815999 CYw = -0.000001 - z force CZ | CZu = -0.102727 CZv = -0.000001 CZw = -5.707655 - x mom. Cl | Clu = -0.000000 Clv = -0.174538 Clw = -0.000004 - y mom. Cm | Cmu = 0.223623 Cmv = -0.000001 Cmw = -8.016401 - z mom. Cn | Cnu = -0.000000 Cnv = 0.279407 Cnw = 0.000000 + x force CX | CXu = -0.006950 CXv = -0.000000 CXw = -0.225297 + y force CY | CYu = 0.000000 CYv = -0.816079 CYw = -0.000000 + z force CZ | CZu = -0.104473 CZv = -0.000000 CZw = -5.707593 + x mom. Cl | Clu = -0.000000 Clv = -0.174710 Clw = -0.000001 + y mom. Cm | Cmu = 0.225033 Cmv = -0.000000 Cmw = -8.017538 + z mom. Cn | Cnu = -0.000000 Cnv = 0.279440 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = -0.000000 CXq = -1.191771 CXr = 0.000000 - y force CY | CYp = -0.310490 CYq = -0.000007 CYr = 0.980085 - z force CZ | CZp = -0.000008 CZq = -27.264530 CZr = 0.000001 - x mom. Cl | Clp = -0.487278 Clq = -0.000023 Clr = 0.165957 - y mom. Cm | Cmp = -0.000016 Cmq = -78.154465 Cmr = 0.000001 - z mom. Cn | Cnp = 0.138928 Cnq = 0.000004 Cnr = -0.515056 + x force CX | CXp = -0.000000 CXq = -1.194593 CXr = 0.000000 + y force CY | CYp = -0.310272 CYq = -0.000001 CYr = 0.980207 + z force CZ | CZp = -0.000001 CZq = -27.269033 CZr = 0.000000 + x mom. Cl | Clp = -0.487283 Clq = -0.000003 Clr = 0.166017 + y mom. Cm | Cmp = -0.000002 Cmq = -78.173744 Cmr = 0.000000 + z mom. Cn | Cnp = 0.138864 Cnq = 0.000001 Cnr = -0.515101 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = 0.000066 CXd2 = -0.000421 CXd3 = 0.000000 CXd4 = -0.000174 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000360 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000586 CZd2 = -0.025324 CZd3 = 0.000000 CZd4 = -0.012102 + x force CX | CXd1 = 0.000056 CXd2 = -0.000437 CXd3 = 0.000000 CXd4 = -0.000175 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000363 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000586 CZd2 = -0.025324 CZd3 = 0.000000 CZd4 = -0.012104 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001938 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000087 Cmd2 = -0.023471 Cmd3 = 0.000000 Cmd4 = -0.058644 - z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000072 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000088 Cmd2 = -0.023468 Cmd3 = 0.000000 Cmd4 = -0.058654 + z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000076 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_02.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_02.txt index 13d202ff25..824fdb6f57 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_02.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_02.txt @@ -13,54 +13,54 @@ Run case: case_02_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = -0.00211 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.02893 - CZtot = -0.15125 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.15125 - CDtot = 0.00211 - CDvis = 0.00000 CDind = 0.0021079 - CLff = 0.15120 CDff = 0.0014688 | Trefftz - CYff = 0.00000 e = 0.5252 | Plane + CXtot = -0.00207 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -0.02823 + CZtot = -0.15211 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.15211 + CDtot = 0.00207 + CDvis = 0.00000 CDind = 0.00207 + CLff = 0.15210 CDff = 0.00150 | Trefftz + CYff = 0.00000 e = 0.5204 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.004216 CXv = -0.000000 CXw = 0.077967 - y force CY | CYu = 0.000000 CYv = -0.822140 CYw = -0.000000 - z force CZ | CZu = -0.302501 CZv = -0.000001 CZw = -5.719002 - x mom. Cl | Clu = -0.000000 Clv = -0.198885 Clw = -0.000004 - y mom. Cm | Cmu = -0.057869 Cmv = -0.000001 Cmw = -8.064782 - z mom. Cn | Cnu = -0.000000 Cnv = 0.277708 Cnw = -0.000000 + x force CX | CXu = -0.004135 CXv = -0.000000 CXw = 0.080713 + y force CY | CYu = 0.000000 CYv = -0.822199 CYw = -0.000000 + z force CZ | CZu = -0.304221 CZv = -0.000000 CZw = -5.718209 + x mom. Cl | Clu = -0.000000 Clv = -0.199055 Clw = -0.000001 + y mom. Cm | Cmu = -0.056469 Cmv = -0.000000 Cmw = -8.065081 + z mom. Cn | Cnu = -0.000000 Cnv = 0.277739 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = -0.198244 CXr = 0.000000 - y force CY | CYp = -0.240175 CYq = -0.000006 CYr = 0.994895 - z force CZ | CZp = -0.000008 CZq = -27.302330 CZr = 0.000001 - x mom. Cl | Clp = -0.486926 Clq = -0.000023 Clr = 0.196278 - y mom. Cm | Cmp = -0.000015 Cmq = -78.475784 Cmr = 0.000002 - z mom. Cn | Cnp = 0.094500 Cnq = 0.000003 Cnr = -0.518562 + x force CX | CXp = 0.000000 CXq = -0.198356 CXr = 0.000000 + y force CY | CYp = -0.239931 CYq = -0.000001 CYr = 0.995013 + z force CZ | CZp = -0.000001 CZq = -27.304304 CZr = 0.000000 + x mom. Cl | Clp = -0.486923 Clq = -0.000003 Clr = 0.196337 + y mom. Cm | Cmp = -0.000002 Cmq = -78.487526 Cmr = 0.000000 + z mom. Cn | Cnp = 0.094433 Cnq = 0.000000 Cnr = -0.518606 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000195 CXd2 = -0.000035 CXd3 = 0.000000 CXd4 = -0.000068 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000337 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000599 CZd2 = -0.025302 CZd3 = 0.000000 CZd4 = -0.012104 + x force CX | CXd1 = -0.000204 CXd2 = -0.000049 CXd3 = 0.000000 CXd4 = -0.000069 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000339 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000599 CZd2 = -0.025301 CZd3 = 0.000000 CZd4 = -0.012105 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001935 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000108 Cmd2 = -0.023429 Cmd3 = 0.000000 Cmd4 = -0.058705 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000109 Cmd2 = -0.023427 Cmd3 = 0.000000 Cmd4 = -0.058713 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000041 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_03.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_03.txt index 31e8eecfe1..08617b363e 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_03.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_03.txt @@ -13,54 +13,54 @@ Run case: case_02_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00593 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.31094 - CZtot = -0.35067 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.35067 - CDtot = 0.00631 - CDvis = 0.00000 CDind = 0.0063121 - CLff = 0.35041 CDff = 0.0052544 | Trefftz - CYff = 0.00000 e = 0.7885 | Plane + CXtot = 0.00609 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.31024 + CZtot = -0.35149 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.35149 + CDtot = 0.00618 + CDvis = 0.00000 CDind = 0.00618 + CLff = 0.35131 CDff = 0.00530 | Trefftz + CYff = 0.00000 e = 0.7855 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.001492 CXv = -0.000000 CXw = 0.382551 - y force CY | CYu = -0.000000 CYv = -0.827280 CYw = 0.000000 - z force CZ | CZu = -0.501907 CZv = -0.000001 CZw = -5.723382 - x mom. Cl | Clu = -0.000000 Clv = -0.222990 Clw = -0.000004 - y mom. Cm | Cmu = -0.339290 Cmv = -0.000002 Cmw = -8.103340 - z mom. Cn | Cnu = -0.000000 Cnv = 0.275670 Cnw = -0.000000 + x force CX | CXu = -0.001316 CXv = 0.000000 CXw = 0.386623 + y force CY | CYu = -0.000000 CYv = -0.827316 CYw = -0.000000 + z force CZ | CZu = -0.503598 CZv = -0.000000 CZw = -5.721858 + x mom. Cl | Clu = -0.000000 Clv = -0.223158 Clw = -0.000001 + y mom. Cm | Cmu = -0.337902 Cmv = -0.000000 Cmw = -8.102798 + z mom. Cn | Cnu = -0.000000 Cnv = 0.275700 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = 0.795523 CXr = 0.000000 - y force CY | CYp = -0.169568 CYq = -0.000006 CYr = 1.008492 - z force CZ | CZp = -0.000008 CZq = -27.306868 CZr = 0.000001 - x mom. Cl | Clp = -0.485981 Clq = -0.000023 Clr = 0.226360 - y mom. Cm | Cmp = -0.000015 Cmq = -78.701515 Cmr = 0.000003 - z mom. Cn | Cnp = 0.049957 Cnq = 0.000003 Cnr = -0.521436 + x force CX | CXp = 0.000000 CXq = 0.798121 CXr = 0.000000 + y force CY | CYp = -0.169298 CYq = -0.000001 CYr = 1.008608 + z force CZ | CZp = -0.000001 CZq = -27.306305 CZr = 0.000000 + x mom. Cl | Clp = -0.485969 Clq = -0.000003 Clr = 0.226418 + y mom. Cm | Cmp = -0.000002 Cmq = -78.705673 Cmr = 0.000001 + z mom. Cn | Cnp = 0.049887 Cnq = 0.000000 Cnr = -0.521478 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000457 CXd2 = 0.000349 CXd3 = 0.000000 CXd4 = 0.000038 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000312 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000611 CZd2 = -0.025219 CZd3 = 0.000000 CZd4 = -0.012076 + x force CX | CXd1 = -0.000467 CXd2 = 0.000337 CXd3 = 0.000000 CXd4 = 0.000037 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000315 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000611 CZd2 = -0.025216 CZd3 = 0.000000 CZd4 = -0.012077 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001927 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000129 Cmd2 = -0.023331 Cmd3 = 0.000000 Cmd4 = -0.058622 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000130 Cmd2 = -0.023328 Cmd3 = 0.000000 Cmd4 = -0.058628 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000007 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_04.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_04.txt index 275714694c..6327dc0fd6 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_04.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_04.txt @@ -13,54 +13,54 @@ Run case: case_02_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.03783 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.73366 - CZtot = -0.64750 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.64834 - CDtot = 0.01875 - CDvis = 0.00000 CDind = 0.0187475 - CLff = 0.64835 CDff = 0.0168225 | Trefftz - CYff = -0.00000 e = 0.8432 | Plane + CXtot = 0.03825 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.73290 + CZtot = -0.64821 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.64908 + CDtot = 0.01839 + CDvis = 0.00000 CDind = 0.01839 + CLff = 0.64924 CDff = 0.01689 | Trefftz + CYff = -0.00000 e = 0.8419 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.002596 CXv = -0.000000 CXw = 0.838437 - y force CY | CYu = -0.000000 CYv = -0.833099 CYw = 0.000001 - z force CZ | CZu = -0.799794 CZv = -0.000002 CZw = -5.716879 - x mom. Cl | Clu = -0.000001 Clv = -0.258629 Clw = -0.000004 - y mom. Cm | Cmu = -0.760541 Cmv = -0.000002 Cmw = -8.142653 - z mom. Cn | Cnu = -0.000000 Cnv = 0.271985 Cnw = -0.000001 + x force CX | CXu = 0.002915 CXv = 0.000000 CXw = 0.844490 + y force CY | CYu = -0.000000 CYv = -0.833101 CYw = -0.000000 + z force CZ | CZu = -0.801438 CZv = -0.000000 CZw = -5.714262 + x mom. Cl | Clu = -0.000000 Clv = -0.258793 Clw = -0.000001 + y mom. Cm | Cmu = -0.759172 Cmv = -0.000000 Cmw = -8.140851 + z mom. Cn | Cnu = -0.000000 Cnv = 0.272012 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 2.283981 CXr = 0.000000 - y force CY | CYp = -0.063295 CYq = -0.000005 CYr = 1.026581 - z force CZ | CZp = -0.000008 CZq = -27.251295 CZr = 0.000002 - x mom. Cl | Clp = -0.483454 Clq = -0.000023 Clr = 0.270954 - y mom. Cm | Cmp = -0.000015 Cmq = -78.860260 Cmr = 0.000005 - z mom. Cn | Cnp = -0.016954 Cnq = 0.000002 Cnr = -0.524554 + x force CX | CXp = 0.000000 CXq = 2.290636 CXr = 0.000000 + y force CY | CYp = -0.062989 CYq = -0.000001 CYr = 1.026690 + z force CZ | CZp = -0.000001 CZq = -27.246950 CZr = 0.000000 + x mom. Cl | Clp = -0.483428 Clq = -0.000003 Clr = 0.271011 + y mom. Cm | Cmp = -0.000002 Cmq = -78.853050 Cmr = 0.000001 + z mom. Cn | Cnp = -0.017029 Cnq = 0.000000 Cnr = -0.524595 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000850 CXd2 = 0.000919 CXd3 = 0.000000 CXd4 = 0.000194 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000275 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000626 CZd2 = -0.024979 CZd3 = 0.000000 CZd4 = -0.011978 + x force CX | CXd1 = -0.000860 CXd2 = 0.000909 CXd3 = 0.000000 CXd4 = 0.000194 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000277 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000626 CZd2 = -0.024975 CZd3 = 0.000000 CZd4 = -0.011979 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001906 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000160 Cmd2 = -0.023077 Cmd3 = 0.000000 Cmd4 = -0.058231 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000162 Cmd2 = -0.023075 Cmd3 = 0.000000 Cmd4 = -0.058233 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000045 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_05.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_05.txt index d474f3f4ee..a945c1a34b 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_05.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_05.txt @@ -13,54 +13,54 @@ Run case: case_02_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.07218 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.01328 - CZtot = -0.84245 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.84497 - CDtot = 0.03103 - CDvis = 0.00000 CDind = 0.0310320 - CLff = 0.84603 CDff = 0.0284063 | Trefftz - CYff = -0.00000 e = 0.8503 | Plane + CXtot = 0.07283 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.01245 + CZtot = -0.84305 Cntot = -0.00000 Cn'tot = 0.00000 + CLtot = 0.84564 + CDtot = 0.03046 + CDvis = 0.00000 CDind = 0.03046 + CLff = 0.84693 CDff = 0.02849 | Trefftz + CYff = -0.00000 e = 0.8494 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.005318 CXv = -0.000000 CXw = 1.141161 - y force CY | CYu = -0.000000 CYv = -0.835710 CYw = 0.000001 - z force CZ | CZu = -0.997217 CZv = -0.000002 CZw = -5.703834 - x mom. Cl | Clu = -0.000001 Clv = -0.282001 Clw = -0.000004 - y mom. Cm | Cmu = -1.040287 Cmv = -0.000003 Cmw = -8.156467 - z mom. Cn | Cnu = -0.000000 Cnv = 0.269114 Cnw = -0.000001 + x force CX | CXu = 0.005732 CXv = 0.000000 CXw = 1.148527 + y force CY | CYu = -0.000000 CYv = -0.835689 CYw = 0.000000 + z force CZ | CZu = -0.998827 CZv = -0.000000 CZw = -5.700493 + x mom. Cl | Clu = -0.000000 Clv = -0.282162 Clw = -0.000001 + y mom. Cm | Cmu = -1.038934 Cmv = -0.000000 Cmw = -8.153828 + z mom. Cn | Cnu = -0.000000 Cnv = 0.269138 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 3.273060 CXr = 0.000000 - y force CY | CYp = 0.007667 CYq = -0.000005 CYr = 1.037079 - z force CZ | CZp = -0.000008 CZq = -27.172739 CZr = 0.000002 - x mom. Cl | Clp = -0.481033 Clq = -0.000023 Clr = 0.300279 - y mom. Cm | Cmp = -0.000015 Cmq = -78.846008 Cmr = 0.000005 - z mom. Cn | Cnp = -0.061548 Cnq = 0.000001 Cnr = -0.525835 + x force CX | CXp = 0.000000 CXq = 3.282409 CXr = 0.000000 + y force CY | CYp = 0.007998 CYq = -0.000001 CYr = 1.037184 + z force CZ | CZp = -0.000001 CZq = -27.165869 CZr = 0.000000 + x mom. Cl | Clp = -0.480998 Clq = -0.000003 Clr = 0.300335 + y mom. Cm | Cmp = -0.000002 Cmq = -78.831230 Cmr = 0.000001 + z mom. Cn | Cnp = -0.061624 Cnq = -0.000000 Cnr = -0.525874 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001110 CXd2 = 0.001292 CXd3 = 0.000000 CXd4 = 0.000297 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000249 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000634 CZd2 = -0.024743 CZd3 = 0.000000 CZd4 = -0.011877 + x force CX | CXd1 = -0.001120 CXd2 = 0.001283 CXd3 = 0.000000 CXd4 = 0.000296 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000252 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000634 CZd2 = -0.024739 CZd3 = 0.000000 CZd4 = -0.011877 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001886 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000181 Cmd2 = -0.022838 Cmd3 = 0.000000 Cmd4 = -0.057793 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000082 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000182 Cmd2 = -0.022836 Cmd3 = 0.000000 Cmd4 = -0.057793 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000078 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_06.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_06.txt index c483d9af23..bb5829629d 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_06.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_02_06.txt @@ -13,54 +13,54 @@ Run case: case_02_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.14289 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.42600 - CZtot = -1.12809 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.13577 - CDtot = 0.05517 - CDvis = 0.00000 CDind = 0.0551705 - CLff = 1.14056 CDff = 0.0514484 | Trefftz - CYff = -0.00000 e = 0.8532 | Plane + CXtot = 0.14397 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.42501 + CZtot = -1.12848 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 1.13633 + CDtot = 0.05417 + CDvis = 0.00000 CDind = 0.05417 + CLff = 1.14145 CDff = 0.05156 | Trefftz + CYff = -0.00000 e = 0.8527 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.009387 CXv = -0.000000 CXw = 1.592526 - y force CY | CYu = -0.000000 CYv = -0.837717 CYw = 0.000002 - z force CZ | CZu = -1.291000 CZv = -0.000002 CZw = -5.671244 - x mom. Cl | Clu = -0.000001 Clv = -0.316405 Clw = -0.000004 - y mom. Cm | Cmu = -1.457425 Cmv = -0.000003 Cmw = -8.158552 - z mom. Cn | Cnu = -0.000000 Cnv = 0.264193 Cnw = -0.000001 + x force CX | CXu = 0.009943 CXv = 0.000000 CXw = 1.601842 + y force CY | CYu = -0.000000 CYv = -0.837662 CYw = -0.000000 + z force CZ | CZu = -1.292555 CZv = -0.000000 CZw = -5.666824 + x mom. Cl | Clu = -0.000000 Clv = -0.316562 Clw = -0.000001 + y mom. Cm | Cmu = -1.456098 Cmv = -0.000000 Cmw = -8.154665 + z mom. Cn | Cnu = -0.000000 Cnv = 0.264214 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000002 CXq = 4.748825 CXr = 0.000000 - y force CY | CYp = 0.114066 CYq = -0.000003 CYr = 1.050454 - z force CZ | CZp = -0.000008 CZq = -26.992868 CZr = 0.000003 - x mom. Cl | Clp = -0.476303 Clq = -0.000023 Clr = 0.343569 - y mom. Cm | Cmp = -0.000015 Cmq = -78.644539 Cmr = 0.000007 - z mom. Cn | Cnp = -0.128280 Cnq = -0.000000 Cnr = -0.526555 + x force CX | CXp = 0.000000 CXq = 4.762196 CXr = 0.000000 + y force CY | CYp = 0.114433 CYq = -0.000001 CYr = 1.050553 + z force CZ | CZp = -0.000001 CZq = -26.982227 CZr = 0.000000 + x mom. Cl | Clp = -0.476255 Clq = -0.000003 Clr = 0.343623 + y mom. Cm | Cmp = -0.000002 Cmq = -78.618454 Cmr = 0.000001 + z mom. Cn | Cnp = -0.128361 Cnq = -0.000000 Cnr = -0.526592 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001495 CXd2 = 0.001835 CXd3 = 0.000000 CXd4 = 0.000447 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000210 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000643 CZd2 = -0.024280 CZd3 = 0.000000 CZd4 = -0.011673 + x force CX | CXd1 = -0.001504 CXd2 = 0.001829 CXd3 = 0.000000 CXd4 = 0.000447 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000213 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000643 CZd2 = -0.024275 CZd3 = 0.000000 CZd4 = -0.011672 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001848 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000211 Cmd2 = -0.022380 Cmd3 = 0.000000 Cmd4 = -0.056877 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000131 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000212 Cmd2 = -0.022378 Cmd3 = 0.000000 Cmd4 = -0.056873 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000127 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_01.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_01.txt index b6d093b53d..75f185c7f0 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_01.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_01.txt @@ -13,54 +13,54 @@ Run case: case_03_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00049 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.25494 - CZtot = 0.04872 Cntot = -0.00000 Cn'tot = -0.00000 + CXtot = 0.00046 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.25568 + CZtot = 0.04783 Cntot = -0.00000 Cn'tot = -0.00000 - CLtot = -0.04871 + CLtot = -0.04781 CDtot = 0.00121 - CDvis = 0.00000 CDind = 0.0012134 - CLff = -0.04864 CDff = 0.0008616 | Trefftz - CYff = 0.00000 e = 0.0927 | Plane - + CDvis = 0.00000 CDind = 0.00121 + CLff = -0.04774 CDff = 0.00088 | Trefftz + CYff = 0.00000 e = 0.0877 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.007037 CXv = -0.000000 CXw = -0.229430 - y force CY | CYu = 0.000000 CYv = -0.820482 CYw = -0.000001 - z force CZ | CZu = -0.104377 CZv = -0.000001 CZw = -5.781112 - x mom. Cl | Clu = -0.000000 Clv = -0.176107 Clw = -0.000004 - y mom. Cm | Cmu = 0.226623 Cmv = -0.000001 Cmw = -8.120303 - z mom. Cn | Cnu = -0.000000 Cnv = 0.281912 Cnw = 0.000000 + x force CX | CXu = -0.007035 CXv = -0.000000 CXw = -0.227647 + y force CY | CYu = 0.000000 CYv = -0.820562 CYw = -0.000000 + z force CZ | CZu = -0.106185 CZv = -0.000000 CZw = -5.781597 + x mom. Cl | Clu = 0.000000 Clv = -0.176283 Clw = -0.000000 + y mom. Cm | Cmu = 0.228059 Cmv = -0.000000 Cmw = -8.121436 + z mom. Cn | Cnu = -0.000000 Cnv = 0.281944 Cnw = 0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = -0.000000 CXq = -1.204196 CXr = 0.000000 - y force CY | CYp = -0.312429 CYq = -0.000007 CYr = 0.985982 - z force CZ | CZp = -0.000009 CZq = -27.588009 CZr = 0.000001 - x mom. Cl | Clp = -0.492659 Clq = -0.000024 Clr = 0.167345 - y mom. Cm | Cmp = -0.000016 Cmq = -79.051575 Cmr = 0.000001 - z mom. Cn | Cnp = 0.139671 Cnq = 0.000004 Cnr = -0.518563 + x force CX | CXp = -0.000000 CXq = -1.205896 CXr = 0.000000 + y force CY | CYp = -0.312204 CYq = -0.000001 CYr = 0.986102 + z force CZ | CZp = -0.000001 CZq = -27.592813 CZr = 0.000000 + x mom. Cl | Clp = -0.492676 Clq = -0.000003 Clr = 0.167406 + y mom. Cm | Cmp = -0.000002 Cmq = -79.068573 Cmr = 0.000000 + z mom. Cn | Cnp = 0.139601 Cnq = 0.000001 Cnr = -0.518606 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = 0.000067 CXd2 = -0.000429 CXd3 = 0.000000 CXd4 = -0.000174 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000364 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000593 CZd2 = -0.025716 CZd3 = 0.000000 CZd4 = -0.012250 + x force CX | CXd1 = 0.000057 CXd2 = -0.000443 CXd3 = 0.000000 CXd4 = -0.000176 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000366 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000593 CZd2 = -0.025716 CZd3 = 0.000000 CZd4 = -0.012252 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001961 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000083 Cmd2 = -0.023860 Cmd3 = 0.000000 Cmd4 = -0.059416 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000072 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000085 Cmd2 = -0.023858 Cmd3 = 0.000000 Cmd4 = -0.059425 + z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000076 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_02.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_02.txt index 7124557a35..f43e9f63bb 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_02.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_02.txt @@ -13,54 +13,54 @@ Run case: case_03_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = -0.00216 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.02926 - CZtot = -0.15336 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.15336 - CDtot = 0.00216 - CDvis = 0.00000 CDind = 0.0021615 - CLff = 0.15331 CDff = 0.0014964 | Trefftz - CYff = 0.00000 e = 0.5300 | Plane + CXtot = -0.00209 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.02855 + CZtot = -0.15427 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.15427 + CDtot = 0.00209 + CDvis = 0.00000 CDind = 0.00209 + CLff = 0.15422 CDff = 0.00153 | Trefftz + CYff = 0.00000 e = 0.5252 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.004323 CXv = -0.000000 CXw = 0.077838 - y force CY | CYu = -0.000000 CYv = -0.826784 CYw = -0.000000 - z force CZ | CZu = -0.306727 CZv = -0.000001 CZw = -5.792707 - x mom. Cl | Clu = -0.000000 Clv = -0.200806 Clw = -0.000004 - y mom. Cm | Cmu = -0.058515 Cmv = -0.000001 Cmw = -8.169252 - z mom. Cn | Cnu = -0.000000 Cnv = 0.280239 Cnw = -0.000000 + x force CX | CXu = -0.004189 CXv = -0.000000 CXw = 0.081612 + y force CY | CYu = -0.000000 CYv = -0.826838 CYw = -0.000000 + z force CZ | CZu = -0.308548 CZv = -0.000000 CZw = -5.793044 + x mom. Cl | Clu = -0.000000 Clv = -0.200983 Clw = -0.000001 + y mom. Cm | Cmu = -0.057099 Cmv = -0.000000 Cmw = -8.169821 + z mom. Cn | Cnu = -0.000000 Cnv = 0.280268 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = -0.204138 CXr = 0.000000 - y force CY | CYp = -0.241449 CYq = -0.000007 CYr = 1.001077 - z force CZ | CZp = -0.000009 CZq = -27.626787 CZr = 0.000001 - x mom. Cl | Clp = -0.492311 Clq = -0.000024 Clr = 0.198141 - y mom. Cm | Cmp = -0.000017 Cmq = -79.376007 Cmr = 0.000002 - z mom. Cn | Cnp = 0.094713 Cnq = 0.000003 Cnr = -0.522171 + x force CX | CXp = 0.000000 CXq = -0.201505 CXr = 0.000000 + y force CY | CYp = -0.241184 CYq = -0.000001 CYr = 1.001193 + z force CZ | CZp = -0.000001 CZq = -27.630119 CZr = 0.000000 + x mom. Cl | Clp = -0.492326 Clq = -0.000003 Clr = 0.198202 + y mom. Cm | Cmp = -0.000002 Cmq = -79.386948 Cmr = 0.000000 + z mom. Cn | Cnp = 0.094634 Cnq = 0.000000 Cnr = -0.522212 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000198 CXd2 = -0.000040 CXd3 = 0.000000 CXd4 = -0.000069 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000340 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000606 CZd2 = -0.025694 CZd3 = 0.000000 CZd4 = -0.012252 + x force CX | CXd1 = -0.000208 CXd2 = -0.000050 CXd3 = 0.000000 CXd4 = -0.000070 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000342 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000607 CZd2 = -0.025693 CZd3 = 0.000000 CZd4 = -0.012253 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001958 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000105 Cmd2 = -0.023818 Cmd3 = 0.000000 Cmd4 = -0.059477 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000106 Cmd2 = -0.023816 Cmd3 = 0.000000 Cmd4 = -0.059484 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000041 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_03.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_03.txt index ee75698777..77951df8d7 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_03.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_03.txt @@ -13,54 +13,54 @@ Run case: case_03_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00592 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.31492 - CZtot = -0.35536 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.35535 - CDtot = 0.00649 - CDvis = 0.00000 CDind = 0.0064885 - CLff = 0.35508 CDff = 0.0053666 | Trefftz - CYff = -0.00000 e = 0.7928 | Plane + CXtot = 0.00615 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.31422 + CZtot = -0.35628 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.35627 + CDtot = 0.00629 + CDvis = 0.00000 CDind = 0.00629 + CLff = 0.35599 CDff = 0.00541 | Trefftz + CYff = -0.00000 e = 0.7897 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.001604 CXv = -0.000000 CXw = 0.385010 - y force CY | CYu = -0.000000 CYv = -0.832078 CYw = -0.000000 - z force CZ | CZu = -0.508702 CZv = -0.000001 CZw = -5.797244 - x mom. Cl | Clu = -0.000000 Clv = -0.225261 Clw = -0.000004 - y mom. Cm | Cmu = -0.343582 Cmv = -0.000002 Cmw = -8.208250 - z mom. Cn | Cnu = -0.000000 Cnv = 0.278224 Cnw = -0.000000 + x force CX | CXu = -0.001339 CXv = 0.000000 CXw = 0.390772 + y force CY | CYu = -0.000000 CYv = -0.832107 CYw = -0.000000 + z force CZ | CZu = -0.510534 CZv = -0.000000 CZw = -5.797436 + x mom. Cl | Clu = -0.000000 Clv = -0.225438 Clw = -0.000001 + y mom. Cm | Cmu = -0.342187 Cmv = -0.000000 Cmw = -8.208254 + z mom. Cn | Cnu = -0.000000 Cnv = 0.278251 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = 0.796168 CXr = 0.000000 - y force CY | CYp = -0.170174 CYq = -0.000007 CYr = 1.014952 - z force CZ | CZp = -0.000009 CZq = -27.631914 CZr = 0.000001 - x mom. Cl | Clp = -0.491364 Clq = -0.000024 Clr = 0.228696 - y mom. Cm | Cmp = -0.000016 Cmq = -79.603752 Cmr = 0.000003 - z mom. Cn | Cnp = 0.049640 Cnq = 0.000003 Cnr = -0.525142 + x force CX | CXp = 0.000000 CXq = 0.803131 CXr = 0.000000 + y force CY | CYp = -0.169871 CYq = -0.000001 CYr = 1.015064 + z force CZ | CZp = -0.000001 CZq = -27.633764 CZr = 0.000000 + x mom. Cl | Clp = -0.491376 Clq = -0.000003 Clr = 0.228757 + y mom. Cm | Cmp = -0.000002 Cmq = -79.608612 Cmr = 0.000000 + z mom. Cn | Cnp = 0.049553 Cnq = 0.000000 Cnr = -0.525182 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000464 CXd2 = 0.000347 CXd3 = 0.000000 CXd4 = 0.000037 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000315 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000619 CZd2 = -0.025609 CZd3 = 0.000000 CZd4 = -0.012223 + x force CX | CXd1 = -0.000474 CXd2 = 0.000342 CXd3 = 0.000000 CXd4 = 0.000036 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000318 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000618 CZd2 = -0.025608 CZd3 = 0.000000 CZd4 = -0.012224 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001950 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000127 Cmd2 = -0.023719 Cmd3 = 0.000000 Cmd4 = -0.059392 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000128 Cmd2 = -0.023716 Cmd3 = 0.000000 Cmd4 = -0.059398 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000006 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_04.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_04.txt index e90c8c7d39..e6af3776f7 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_04.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_04.txt @@ -13,54 +13,54 @@ Run case: case_03_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.03805 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.74311 - CZtot = -0.65602 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.65684 - CDtot = 0.01927 - CDvis = 0.00000 CDind = 0.0192735 - CLff = 0.65685 CDff = 0.0171926 | Trefftz - CYff = -0.00000 e = 0.8468 | Plane + CXtot = 0.03866 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.74239 + CZtot = -0.65694 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.65781 + CDtot = 0.01875 + CDvis = 0.00000 CDind = 0.01875 + CLff = 0.65776 CDff = 0.01727 | Trefftz + CYff = -0.00000 e = 0.8455 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.002477 CXv = -0.000000 CXw = 0.844772 - y force CY | CYu = -0.000000 CYv = -0.838118 CYw = 0.000000 - z force CZ | CZu = -0.810427 CZv = -0.000002 CZw = -5.790808 - x mom. Cl | Clu = -0.000001 Clv = -0.261419 Clw = -0.000004 - y mom. Cm | Cmu = -0.770290 Cmv = -0.000002 Cmw = -8.247984 - z mom. Cn | Cnu = -0.000000 Cnv = 0.274567 Cnw = -0.000001 + x force CX | CXu = 0.002940 CXv = 0.000000 CXw = 0.853502 + y force CY | CYu = -0.000000 CYv = -0.838108 CYw = -0.000000 + z force CZ | CZu = -0.812270 CZv = -0.000000 CZw = -5.790779 + x mom. Cl | Clu = -0.000000 Clv = -0.261596 Clw = -0.000001 + y mom. Cm | Cmu = -0.768928 Cmv = -0.000000 Cmw = -8.247142 + z mom. Cn | Cnu = -0.000000 Cnv = 0.274590 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 2.294428 CXr = 0.000000 - y force CY | CYp = -0.062900 CYq = -0.000005 CYr = 1.033441 - z force CZ | CZp = -0.000009 CZq = -27.576487 CZr = 0.000002 - x mom. Cl | Clp = -0.488820 Clq = -0.000024 Clr = 0.273995 - y mom. Cm | Cmp = -0.000016 Cmq = -79.763451 Cmr = 0.000005 - z mom. Cn | Cnp = -0.018067 Cnq = 0.000002 Cnr = -0.528399 + x force CX | CXp = 0.000000 CXq = 2.307869 CXr = 0.000000 + y force CY | CYp = -0.062539 CYq = -0.000001 CYr = 1.033547 + z force CZ | CZp = -0.000001 CZq = -27.576113 CZr = 0.000000 + x mom. Cl | Clp = -0.488830 Clq = -0.000003 Clr = 0.274055 + y mom. Cm | Cmp = -0.000002 Cmq = -79.759201 Cmr = 0.000001 + z mom. Cn | Cnp = -0.018166 Cnq = 0.000000 Cnr = -0.528437 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000862 CXd2 = 0.000921 CXd3 = 0.000000 CXd4 = 0.000193 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000277 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000634 CZd2 = -0.025366 CZd3 = 0.000000 CZd4 = -0.012125 + x force CX | CXd1 = -0.000872 CXd2 = 0.000923 CXd3 = 0.000000 CXd4 = 0.000192 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000280 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000633 CZd2 = -0.025364 CZd3 = 0.000000 CZd4 = -0.012125 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001928 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000159 Cmd2 = -0.023462 Cmd3 = 0.000000 Cmd4 = -0.058994 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000160 Cmd2 = -0.023458 Cmd3 = 0.000000 Cmd4 = -0.058997 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000045 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_05.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_05.txt index b50d799695..86d2a8f442 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_05.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_05.txt @@ -13,54 +13,54 @@ Run case: case_03_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.07266 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.02634 - CZtot = -0.85349 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.85599 - CDtot = 0.03190 - CDvis = 0.00000 CDind = 0.0318987 - CLff = 0.85708 CDff = 0.0290343 | Trefftz - CYff = -0.00000 e = 0.8537 | Plane + CXtot = 0.07360 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.02559 + CZtot = -0.85440 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.85700 + CDtot = 0.03107 + CDvis = 0.00000 CDind = 0.03107 + CLff = 0.85799 CDff = 0.02912 | Trefftz + CYff = -0.00000 e = 0.8529 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.005195 CXv = -0.000000 CXw = 1.150072 - y force CY | CYu = -0.000000 CYv = -0.840869 CYw = 0.000001 - z force CZ | CZu = -1.010394 CZv = -0.000002 CZw = -5.777696 - x mom. Cl | Clu = -0.000001 Clv = -0.285132 Clw = -0.000004 - y mom. Cm | Cmu = -1.053661 Cmv = -0.000003 Cmw = -8.261917 - z mom. Cn | Cnu = -0.000000 Cnv = 0.271710 Cnw = -0.000001 + x force CX | CXu = 0.005788 CXv = 0.000000 CXw = 1.160767 + y force CY | CYu = -0.000000 CYv = -0.840833 CYw = -0.000000 + z force CZ | CZu = -1.012242 CZv = -0.000000 CZw = -5.777519 + x mom. Cl | Clu = -0.000000 Clv = -0.285309 Clw = -0.000001 + y mom. Cm | Cmu = -1.052324 Cmv = -0.000000 Cmw = -8.260511 + z mom. Cn | Cnu = -0.000000 Cnv = 0.271730 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 3.290028 CXr = 0.000000 - y force CY | CYp = 0.008729 CYq = -0.000005 CYr = 1.044197 - z force CZ | CZp = -0.000009 CZq = -27.497524 CZr = 0.000003 - x mom. Cl | Clp = -0.486379 Clq = -0.000024 Clr = 0.303784 - y mom. Cm | Cmp = -0.000016 Cmq = -79.748459 Cmr = 0.000006 - z mom. Cn | Cnp = -0.063188 Cnq = 0.000001 Cnr = -0.529765 + x force CX | CXp = 0.000000 CXq = 3.307767 CXr = 0.000000 + y force CY | CYp = 0.009129 CYq = -0.000001 CYr = 1.044297 + z force CZ | CZp = -0.000001 CZq = -27.495670 CZr = 0.000000 + x mom. Cl | Clp = -0.486387 Clq = -0.000003 Clr = 0.303845 + y mom. Cm | Cmp = -0.000002 Cmq = -79.738136 Cmr = 0.000001 + z mom. Cn | Cnp = -0.063295 Cnq = 0.000000 Cnr = -0.529802 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001126 CXd2 = 0.001296 CXd3 = 0.000000 CXd4 = 0.000295 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000251 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000642 CZd2 = -0.025127 CZd3 = 0.000000 CZd4 = -0.012022 + x force CX | CXd1 = -0.001136 CXd2 = 0.001302 CXd3 = 0.000000 CXd4 = 0.000295 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000254 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000641 CZd2 = -0.025125 CZd3 = 0.000000 CZd4 = -0.012022 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001909 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000180 Cmd2 = -0.023220 Cmd3 = 0.000000 Cmd4 = -0.058550 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000082 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000181 Cmd2 = -0.023216 Cmd3 = 0.000000 Cmd4 = -0.058551 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000079 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_06.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_06.txt index bdfee5c017..992445dd31 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_06.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_03_06.txt @@ -13,54 +13,54 @@ Run case: case_03_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.14394 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.44440 - CZtot = -1.14283 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = 1.15047 - CDtot = 0.05670 - CDvis = 0.00000 CDind = 0.0567018 - CLff = 1.15539 CDff = 0.0525895 | Trefftz - CYff = -0.00000 e = 0.8565 | Plane + CXtot = 0.14551 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.44356 + CZtot = -1.14371 Cntot = -0.00000 Cn'tot = 0.00000 + CLtot = 1.15160 + CDtot = 0.05531 + CDvis = 0.00000 CDind = 0.05531 + CLff = 1.15629 CDff = 0.05270 | Trefftz + CYff = -0.00000 e = 0.8560 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.009259 CXv = -0.000000 CXw = 1.605278 - y force CY | CYu = -0.000000 CYv = -0.843073 CYw = 0.000001 - z force CZ | CZu = -1.307960 CZv = -0.000002 CZw = -5.744837 - x mom. Cl | Clu = -0.000001 Clv = -0.320042 Clw = -0.000004 - y mom. Cm | Cmu = -1.476202 Cmv = -0.000003 Cmw = -8.263943 - z mom. Cn | Cnu = -0.000000 Cnv = 0.266806 Cnw = -0.000001 + x force CX | CXu = 0.010046 CXv = 0.000000 CXw = 1.618896 + y force CY | CYu = -0.000000 CYv = -0.843000 CYw = 0.000000 + z force CZ | CZu = -1.309812 CZv = -0.000000 CZw = -5.744440 + x mom. Cl | Clu = -0.000000 Clv = -0.320219 Clw = -0.000001 + y mom. Cm | Cmu = -1.474906 Cmv = -0.000000 Cmw = -8.261694 + z mom. Cn | Cnu = -0.000000 Cnv = 0.266822 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000002 CXq = 4.775534 CXr = 0.000000 - y force CY | CYp = 0.116127 CYq = -0.000004 CYr = 1.057940 - z force CZ | CZp = -0.000009 CZq = -27.316311 CZr = 0.000003 - x mom. Cl | Clp = -0.481608 Clq = -0.000023 Clr = 0.347763 - y mom. Cm | Cmp = -0.000016 Cmq = -79.543846 Cmr = 0.000007 - z mom. Cn | Cnp = -0.130709 Cnq = -0.000000 Cnr = -0.530605 + x force CX | CXp = 0.000000 CXq = 4.799678 CXr = 0.000000 + y force CY | CYp = 0.116583 CYq = -0.000001 CYr = 1.058035 + z force CZ | CZp = -0.000001 CZq = -27.312233 CZr = 0.000000 + x mom. Cl | Clp = -0.481613 Clq = -0.000003 Clr = 0.347823 + y mom. Cm | Cmp = -0.000002 Cmq = -79.524414 Cmr = 0.000001 + z mom. Cn | Cnp = -0.130828 Cnq = -0.000000 Cnr = -0.530639 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001516 CXd2 = 0.001844 CXd3 = 0.000000 CXd4 = 0.000445 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000212 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000652 CZd2 = -0.024657 CZd3 = 0.000000 CZd4 = -0.011815 + x force CX | CXd1 = -0.001525 CXd2 = 0.001856 CXd3 = 0.000000 CXd4 = 0.000445 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000215 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000650 CZd2 = -0.024654 CZd3 = 0.000000 CZd4 = -0.011815 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001870 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000210 Cmd2 = -0.022754 Cmd3 = 0.000000 Cmd4 = -0.057621 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000132 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000211 Cmd2 = -0.022751 Cmd3 = 0.000000 Cmd4 = -0.057618 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000128 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_01.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_01.txt index 0947a39288..3fbde4c132 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_01.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_01.txt @@ -13,54 +13,54 @@ Run case: case_04_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00048 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.26769 - CZtot = 0.05045 Cntot = -0.00000 Cn'tot = -0.00000 + CXtot = 0.00044 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.26853 + CZtot = 0.04952 Cntot = -0.00000 Cn'tot = -0.00000 - CLtot = -0.05044 + CLtot = -0.04950 CDtot = 0.00128 - CDvis = 0.00000 CDind = 0.0012833 - CLff = -0.05038 CDff = 0.0009144 | Trefftz - CYff = 0.00000 e = 0.0936 | Plane - + CDvis = 0.00000 CDind = 0.00128 + CLff = -0.04942 CDff = 0.00093 | Trefftz + CYff = 0.00000 e = 0.0886 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.007402 CXv = -0.000000 CXw = -0.239334 - y force CY | CYu = 0.000000 CYv = -0.837418 CYw = -0.000001 - z force CZ | CZu = -0.110916 CZv = -0.000001 CZw = -6.067360 - x mom. Cl | Clu = -0.000000 Clv = -0.182086 Clw = -0.000005 - y mom. Cm | Cmu = 0.238077 Cmv = -0.000001 Cmw = -8.522898 - z mom. Cn | Cnu = -0.000000 Cnv = 0.291389 Cnw = 0.000000 + x force CX | CXu = -0.007395 CXv = -0.000000 CXw = -0.237241 + y force CY | CYu = -0.000000 CYv = -0.837487 CYw = -0.000000 + z force CZ | CZu = -0.112777 CZv = -0.000000 CZw = -6.067167 + x mom. Cl | Clu = -0.000000 Clv = -0.182267 Clw = -0.000001 + y mom. Cm | Cmu = 0.239719 Cmv = -0.000000 Cmw = -8.524026 + z mom. Cn | Cnu = -0.000000 Cnv = 0.291416 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = -0.000000 CXq = -1.249763 CXr = 0.000000 - y force CY | CYp = -0.319718 CYq = -0.000008 CYr = 1.008286 - z force CZ | CZp = -0.000010 CZq = -28.843513 CZr = 0.000001 - x mom. Cl | Clp = -0.513370 Clq = -0.000027 Clr = 0.172627 - y mom. Cm | Cmp = -0.000018 Cmq = -82.517746 Cmr = 0.000001 - z mom. Cn | Cnp = 0.142417 Cnq = 0.000004 Cnr = -0.531830 + x force CX | CXp = -0.000000 CXq = -1.250962 CXr = -0.000000 + y force CY | CYp = -0.319449 CYq = -0.000001 CYr = 1.008398 + z force CZ | CZp = -0.000001 CZq = -28.847887 CZr = 0.000000 + x mom. Cl | Clp = -0.513375 Clq = -0.000003 Clr = 0.172685 + y mom. Cm | Cmp = -0.000002 Cmq = -82.537949 Cmr = 0.000000 + z mom. Cn | Cnp = 0.142330 Cnq = 0.000001 Cnr = -0.531868 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = 0.000068 CXd2 = -0.000460 CXd3 = 0.000000 CXd4 = -0.000177 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000376 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000619 CZd2 = -0.027261 CZd3 = 0.000000 CZd4 = -0.012826 + x force CX | CXd1 = 0.000058 CXd2 = -0.000475 CXd3 = 0.000000 CXd4 = -0.000178 + y force CY | CYd1 = 0.000000 CYd2 = 0.000000 CYd3 = 0.000379 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000619 CZd2 = -0.027260 CZd3 = 0.000000 CZd4 = -0.012828 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002050 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000069 Cmd2 = -0.025404 Cmd3 = 0.000000 Cmd4 = -0.062427 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000074 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000070 Cmd2 = -0.025401 Cmd3 = 0.000000 Cmd4 = -0.062438 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000077 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_02.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_02.txt index 2fa16f6467..1dd4b9f496 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_02.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_02.txt @@ -13,54 +13,54 @@ Run case: case_04_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = -0.00233 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.03060 - CZtot = -0.16165 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.16165 - CDtot = 0.00233 - CDvis = 0.00000 CDind = 0.0023262 - CLff = 0.16158 CDff = 0.0016067 | Trefftz - CYff = 0.00000 e = 0.5483 | Plane + CXtot = -0.00224 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.02978 + CZtot = -0.16256 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.16256 + CDtot = 0.00224 + CDvis = 0.00000 CDind = 0.00224 + CLff = 0.16254 CDff = 0.00164 | Trefftz + CYff = 0.00000 e = 0.5433 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.004652 CXv = -0.000000 CXw = 0.078865 - y force CY | CYu = -0.000000 CYv = -0.844359 CYw = -0.000000 - z force CZ | CZu = -0.323303 CZv = -0.000002 CZw = -6.080036 - x mom. Cl | Clu = -0.000000 Clv = -0.208162 Clw = -0.000005 - y mom. Cm | Cmu = -0.061206 Cmv = -0.000001 Cmw = -8.574489 - z mom. Cn | Cnu = -0.000000 Cnv = 0.289821 Cnw = -0.000000 + x force CX | CXu = -0.004487 CXv = -0.000000 CXw = 0.083400 + y force CY | CYu = -0.000000 CYv = -0.844396 CYw = -0.000000 + z force CZ | CZu = -0.325122 CZv = -0.000000 CZw = -6.078799 + x mom. Cl | Clu = -0.000000 Clv = -0.208341 Clw = -0.000001 + y mom. Cm | Cmu = -0.059567 Cmv = -0.000000 Cmw = -8.574608 + z mom. Cn | Cnu = -0.000000 Cnv = 0.289846 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = -0.221527 CXr = 0.000000 - y force CY | CYp = -0.246157 CYq = -0.000007 CYr = 1.024500 - z force CZ | CZp = -0.000010 CZq = -28.887135 CZr = 0.000001 - x mom. Cl | Clp = -0.513042 Clq = -0.000027 Clr = 0.205288 - y mom. Cm | Cmp = -0.000018 Cmq = -82.858521 Cmr = 0.000002 - z mom. Cn | Cnp = 0.095401 Cnq = 0.000003 Cnr = -0.535841 + x force CX | CXp = 0.000000 CXq = -0.218009 CXr = 0.000000 + y force CY | CYp = -0.245831 CYq = -0.000001 CYr = 1.024608 + z force CZ | CZp = -0.000001 CZq = -28.888634 CZr = 0.000000 + x mom. Cl | Clp = -0.513036 Clq = -0.000003 Clr = 0.205345 + y mom. Cm | Cmp = -0.000002 Cmq = -82.870773 Cmr = 0.000000 + z mom. Cn | Cnp = 0.095305 Cnq = 0.000000 Cnr = -0.535878 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000211 CXd2 = -0.000057 CXd3 = 0.000000 CXd4 = -0.000072 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000352 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000633 CZd2 = -0.027239 CZd3 = 0.000000 CZd4 = -0.012827 + x force CX | CXd1 = -0.000222 CXd2 = -0.000067 CXd3 = 0.000000 CXd4 = -0.000073 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000354 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000632 CZd2 = -0.027237 CZd3 = 0.000000 CZd4 = -0.012829 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002046 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000092 Cmd2 = -0.025363 Cmd3 = 0.000000 Cmd4 = -0.062489 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000093 Cmd2 = -0.025359 Cmd3 = 0.000000 Cmd4 = -0.062497 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000042 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_03.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_03.txt index 6c7a6c7235..50592290bb 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_03.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_03.txt @@ -13,54 +13,54 @@ Run case: case_04_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00598 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.33044 - CZtot = -0.37367 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.37365 - CDtot = 0.00707 - CDvis = 0.00000 CDind = 0.0070657 - CLff = 0.37334 CDff = 0.0058163 | Trefftz - CYff = -0.00000 e = 0.8086 | Plane + CXtot = 0.00626 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.32961 + CZtot = -0.37452 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.37451 + CDtot = 0.00681 + CDvis = 0.00000 CDind = 0.00681 + CLff = 0.37430 CDff = 0.00587 | Trefftz + CYff = 0.00000 e = 0.8056 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.001897 CXv = -0.000000 CXw = 0.396968 - y force CY | CYu = -0.000000 CYv = -0.850271 CYw = -0.000000 - z force CZ | CZu = -0.535297 CZv = -0.000002 CZw = -6.085303 - x mom. Cl | Clu = -0.000000 Clv = -0.233985 Clw = -0.000005 - y mom. Cm | Cmu = -0.360414 Cmv = -0.000002 Cmw = -8.615633 - z mom. Cn | Cnu = -0.000000 Cnv = 0.287900 Cnw = -0.000000 + x force CX | CXu = -0.001574 CXv = -0.000000 CXw = 0.403939 + y force CY | CYu = -0.000000 CYv = -0.850276 CYw = -0.000000 + z force CZ | CZu = -0.537071 CZv = -0.000000 CZw = -6.083027 + x mom. Cl | Clu = -0.000000 Clv = -0.234161 Clw = -0.000001 + y mom. Cm | Cmu = -0.358780 Cmv = -0.000000 Cmw = -8.614743 + z mom. Cn | Cnu = -0.000000 Cnv = 0.287922 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = 0.806977 CXr = 0.000000 - y force CY | CYp = -0.172296 CYq = -0.000006 CYr = 1.039466 - z force CZ | CZp = -0.000009 CZq = -28.895561 CZr = 0.000002 - x mom. Cl | Clp = -0.512089 Clq = -0.000027 Clr = 0.237699 - y mom. Cm | Cmp = -0.000018 Cmq = -83.098343 Cmr = 0.000003 - z mom. Cn | Cnp = 0.048267 Cnq = 0.000003 Cnr = -0.539199 + x force CX | CXp = 0.000000 CXq = 0.815207 CXr = 0.000000 + y force CY | CYp = -0.171914 CYq = -0.000001 CYr = 1.039568 + z force CZ | CZp = -0.000001 CZq = -28.894178 CZr = 0.000000 + x mom. Cl | Clp = -0.512073 Clq = -0.000003 Clr = 0.237755 + y mom. Cm | Cmp = -0.000002 Cmq = -83.102646 Cmr = 0.000000 + z mom. Cn | Cnp = 0.048165 Cnq = 0.000000 Cnr = -0.539235 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000492 CXd2 = 0.000345 CXd3 = 0.000000 CXd4 = 0.000033 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000326 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000646 CZd2 = -0.027151 CZd3 = 0.000000 CZd4 = -0.012797 + x force CX | CXd1 = -0.000503 CXd2 = 0.000339 CXd3 = 0.000000 CXd4 = 0.000032 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000329 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000644 CZd2 = -0.027147 CZd3 = 0.000000 CZd4 = -0.012798 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002038 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000115 Cmd2 = -0.025259 Cmd3 = 0.000000 Cmd4 = -0.062398 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000116 Cmd2 = -0.025256 Cmd3 = 0.000000 Cmd4 = -0.062404 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000006 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_04.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_04.txt index e3f825a08d..8e5a53a30d 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_04.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_04.txt @@ -13,54 +13,54 @@ Run case: case_04_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.03916 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.77989 - CZtot = -0.68929 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.69008 - CDtot = 0.02106 - CDvis = 0.00000 CDind = 0.0210622 - CLff = 0.69005 CDff = 0.0186758 | Trefftz - CYff = -0.00000 e = 0.8603 | Plane + CXtot = 0.03990 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.77898 + CZtot = -0.68998 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.69083 + CDtot = 0.02038 + CDvis = 0.00000 CDind = 0.02038 + CLff = 0.69101 CDff = 0.01875 | Trefftz + CYff = -0.00000 e = 0.8591 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.002239 CXv = -0.000000 CXw = 0.873094 - y force CY | CYu = -0.000000 CYv = -0.857194 CYw = 0.000001 - z force CZ | CZu = -0.851983 CZv = -0.000002 CZw = -6.079304 - x mom. Cl | Clu = -0.000001 Clv = -0.272174 Clw = -0.000005 - y mom. Cm | Cmu = -0.808289 Cmv = -0.000003 Cmw = -8.657656 - z mom. Cn | Cnu = -0.000000 Cnv = 0.284363 Cnw = -0.000001 + x force CX | CXu = 0.002799 CXv = -0.000000 CXw = 0.883703 + y force CY | CYu = -0.000000 CYv = -0.857151 CYw = -0.000000 + z force CZ | CZu = -0.853687 CZv = -0.000000 CZw = -6.075473 + x mom. Cl | Clu = -0.000000 Clv = -0.272347 Clw = -0.000001 + y mom. Cm | Cmu = -0.806666 Cmv = -0.000000 Cmw = -8.655253 + z mom. Cn | Cnu = -0.000000 Cnv = 0.284380 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 2.347500 CXr = 0.000000 - y force CY | CYp = -0.061139 CYq = -0.000006 CYr = 1.059534 - z force CZ | CZp = -0.000009 CZq = -28.842196 CZr = 0.000002 - x mom. Cl | Clp = -0.509490 Clq = -0.000027 Clr = 0.285759 - y mom. Cm | Cmp = -0.000017 Cmq = -83.268173 Cmr = 0.000005 - z mom. Cn | Cnp = -0.022525 Cnq = 0.000002 Cnr = -0.543004 + x force CX | CXp = 0.000000 CXq = 2.362779 CXr = 0.000000 + y force CY | CYp = -0.060675 CYq = -0.000001 CYr = 1.059630 + z force CZ | CZp = -0.000001 CZq = -28.836508 CZr = 0.000000 + x mom. Cl | Clp = -0.509459 Clq = -0.000004 Clr = 0.285815 + y mom. Cm | Cmp = -0.000002 Cmq = -83.260551 Cmr = 0.000001 + z mom. Cn | Cnp = -0.022639 Cnq = 0.000000 Cnr = -0.543038 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000913 CXd2 = 0.000940 CXd3 = 0.000000 CXd4 = 0.000188 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000287 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000662 CZd2 = -0.026895 CZd3 = 0.000000 CZd4 = -0.012694 + x force CX | CXd1 = -0.000924 CXd2 = 0.000941 CXd3 = 0.000000 CXd4 = 0.000188 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000290 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000659 CZd2 = -0.026889 CZd3 = 0.000000 CZd4 = -0.012695 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002016 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000149 Cmd2 = -0.024990 Cmd3 = 0.000000 Cmd4 = -0.061976 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000050 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000150 Cmd2 = -0.024986 Cmd3 = 0.000000 Cmd4 = -0.061978 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000047 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_05.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_05.txt index 2d939de441..450aaff431 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_05.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_05.txt @@ -13,54 +13,54 @@ Run case: case_04_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.07495 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.07719 - CZtot = -0.89661 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.89906 - CDtot = 0.03488 - CDvis = 0.00000 CDind = 0.0348820 - CLff = 0.90020 CDff = 0.0315514 | Trefftz - CYff = -0.00000 e = 0.8666 | Plane + CXtot = 0.07609 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.07618 + CZtot = -0.89713 Cntot = -0.00000 Cn'tot = 0.00000 + CLtot = 0.89972 + CDtot = 0.03381 + CDvis = 0.00000 CDind = 0.03381 + CLff = 0.90115 CDff = 0.03165 | Trefftz + CYff = -0.00000 e = 0.8658 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.004993 CXv = -0.000000 CXw = 1.189263 - y force CY | CYu = -0.000000 CYv = -0.860505 CYw = 0.000001 - z force CZ | CZu = -1.061864 CZv = -0.000002 CZw = -6.066045 - x mom. Cl | Clu = -0.000001 Clv = -0.297225 Clw = -0.000005 - y mom. Cm | Cmu = -1.105717 Cmv = -0.000003 Cmw = -8.672490 - z mom. Cn | Cnu = -0.000000 Cnv = 0.281570 Cnw = -0.000001 + x force CX | CXu = 0.005710 CXv = -0.000000 CXw = 1.202280 + y force CY | CYu = -0.000000 CYv = -0.860431 CYw = -0.000000 + z force CZ | CZu = -1.063518 CZv = -0.000000 CZw = -6.061182 + x mom. Cl | Clu = -0.000000 Clv = -0.297395 Clw = -0.000001 + y mom. Cm | Cmu = -1.104104 Cmv = -0.000000 Cmw = -8.669086 + z mom. Cn | Cnu = -0.000000 Cnv = 0.281584 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 3.371202 CXr = 0.000000 - y force CY | CYp = 0.013077 CYq = -0.000005 CYr = 1.071303 - z force CZ | CZp = -0.000009 CZq = -28.762680 CZr = 0.000003 - x mom. Cl | Clp = -0.506981 Clq = -0.000027 Clr = 0.317373 - y mom. Cm | Cmp = -0.000017 Cmq = -83.254616 Cmr = 0.000006 - z mom. Cn | Cnp = -0.069697 Cnq = 0.000001 Cnr = -0.544713 + x force CX | CXp = 0.000000 CXq = 3.391158 CXr = 0.000000 + y force CY | CYp = 0.013597 CYq = -0.000001 CYr = 1.071393 + z force CZ | CZp = -0.000001 CZq = -28.754128 CZr = 0.000000 + x mom. Cl | Clp = -0.506940 Clq = -0.000003 Clr = 0.317428 + y mom. Cm | Cmp = -0.000002 Cmq = -83.239044 Cmr = 0.000001 + z mom. Cn | Cnp = -0.069819 Cnq = 0.000000 Cnr = -0.544747 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001192 CXd2 = 0.001329 CXd3 = 0.000000 CXd4 = 0.000290 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000261 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000671 CZd2 = -0.026643 CZd3 = 0.000000 CZd4 = -0.012587 + x force CX | CXd1 = -0.001203 CXd2 = 0.001335 CXd3 = 0.000000 CXd4 = 0.000290 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000264 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000667 CZd2 = -0.026636 CZd3 = 0.000000 CZd4 = -0.012587 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001995 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000172 Cmd2 = -0.024735 Cmd3 = 0.000000 Cmd4 = -0.061507 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000085 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000172 Cmd2 = -0.024731 Cmd3 = 0.000000 Cmd4 = -0.061507 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000081 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_06.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_06.txt index 1c2aaaa48a..44bd8eae16 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_06.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_04_06.txt @@ -13,54 +13,54 @@ Run case: case_04_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.14867 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.51603 - CZtot = -1.20040 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = 1.20798 - CDtot = 0.06203 - CDvis = 0.00000 CDind = 0.0620319 - CLff = 1.21327 CDff = 0.0571619 | Trefftz - CYff = -0.00000 e = 0.8690 | Plane + CXtot = 0.15058 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.51482 + CZtot = -1.20062 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 1.20853 + CDtot = 0.06019 + CDvis = 0.00000 CDind = 0.06019 + CLff = 1.21422 CDff = 0.05728 | Trefftz + CYff = -0.00000 e = 0.8685 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.009113 CXv = -0.000000 CXw = 1.660679 - y force CY | CYu = -0.000000 CYv = -0.863506 CYw = 0.000002 - z force CZ | CZu = -1.374179 CZv = -0.000002 CZw = -6.032305 - x mom. Cl | Clu = -0.000001 Clv = -0.334114 Clw = -0.000005 - y mom. Cm | Cmu = -1.549220 Cmv = -0.000004 Cmw = -8.674930 - z mom. Cn | Cnu = -0.000000 Cnv = 0.276740 Cnw = -0.000002 + x force CX | CXu = 0.010063 CXv = 0.000000 CXw = 1.677279 + y force CY | CYu = -0.000000 CYv = -0.863384 CYw = 0.000000 + z force CZ | CZu = -1.375755 CZv = -0.000000 CZw = -6.025908 + x mom. Cl | Clu = -0.000000 Clv = -0.334280 Clw = -0.000001 + y mom. Cm | Cmu = -1.547626 Cmv = -0.000000 Cmw = -8.670029 + z mom. Cn | Cnu = -0.000000 Cnv = 0.276749 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000002 CXq = 4.898662 CXr = 0.000000 - y force CY | CYp = 0.124344 CYq = -0.000004 CYr = 1.086505 - z force CZ | CZp = -0.000009 CZq = -28.577751 CZr = 0.000004 - x mom. Cl | Clp = -0.502060 Clq = -0.000027 Clr = 0.364056 - y mom. Cm | Cmp = -0.000017 Cmq = -83.044128 Cmr = 0.000008 - z mom. Cn | Cnp = -0.140278 Cnq = -0.000000 Cnr = -0.546033 + x force CX | CXp = 0.000000 CXq = 4.925585 CXr = 0.000000 + y force CY | CYp = 0.124944 CYq = -0.000002 CYr = 1.086587 + z force CZ | CZp = -0.000001 CZq = -28.564917 CZr = 0.000000 + x mom. Cl | Clp = -0.502005 Clq = -0.000004 Clr = 0.364109 + y mom. Cm | Cmp = -0.000002 Cmq = -83.016663 Cmr = 0.000001 + z mom. Cn | Cnp = -0.140411 Cnq = 0.000000 Cnr = -0.546065 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001603 CXd2 = 0.001896 CXd3 = 0.000000 CXd4 = 0.000439 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000220 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000682 CZd2 = -0.026147 CZd3 = 0.000000 CZd4 = -0.012371 + x force CX | CXd1 = -0.001614 CXd2 = 0.001909 CXd3 = 0.000000 CXd4 = 0.000439 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000223 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000676 CZd2 = -0.026139 CZd3 = 0.000000 CZd4 = -0.012370 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001955 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000205 Cmd2 = -0.024244 Cmd3 = 0.000000 Cmd4 = -0.060527 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000135 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000205 Cmd2 = -0.024239 Cmd3 = 0.000000 Cmd4 = -0.060523 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000132 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_01.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_01.txt index edc08c1e6e..3dd0042bb5 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_01.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_01.txt @@ -13,54 +13,54 @@ Run case: case_05_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00043 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.29265 - CZtot = 0.05367 Cntot = -0.00000 Cn'tot = -0.00000 + CXtot = 0.00040 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.29369 + CZtot = 0.05263 Cntot = -0.00000 Cn'tot = -0.00000 - CLtot = -0.05366 + CLtot = -0.05261 CDtot = 0.00144 - CDvis = 0.00000 CDind = 0.0014392 - CLff = -0.05361 CDff = 0.0010232 | Trefftz - CYff = 0.00000 e = 0.0948 | Plane - + CDvis = 0.00000 CDind = 0.00144 + CLff = -0.05256 CDff = 0.00104 | Trefftz + CYff = 0.00000 e = 0.0895 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.008152 CXv = -0.000000 CXw = -0.258320 - y force CY | CYu = -0.000000 CYv = -0.869035 CYw = -0.000001 - z force CZ | CZu = -0.124593 CZv = -0.000001 CZw = -6.643846 - x mom. Cl | Clu = -0.000000 Clv = -0.193488 Clw = -0.000006 - y mom. Cm | Cmu = 0.260043 Cmv = 0.000001 Cmw = -9.324572 - z mom. Cn | Cnu = -0.000000 Cnv = 0.309144 Cnw = -0.000000 + x force CX | CXu = -0.008180 CXv = -0.000000 CXw = -0.257038 + y force CY | CYu = 0.000000 CYv = -0.869112 CYw = -0.000000 + z force CZ | CZu = -0.126719 CZv = -0.000000 CZw = -6.644833 + x mom. Cl | Clu = -0.000000 Clv = -0.193688 Clw = -0.000001 + y mom. Cm | Cmu = 0.262058 Cmv = 0.000000 Cmw = -9.326015 + z mom. Cn | Cnu = -0.000000 Cnv = 0.309166 Cnw = 0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = -0.000000 CXq = -1.332371 CXr = -0.000000 - y force CY | CYp = -0.333142 CYq = -0.000006 CYr = 1.050112 - z force CZ | CZp = -0.000011 CZq = -31.355049 CZr = 0.000000 - x mom. Cl | Clp = -0.553717 Clq = -0.000032 Clr = 0.182663 - y mom. Cm | Cmp = -0.000021 Cmq = -89.391586 Cmr = -0.000001 - z mom. Cn | Cnp = 0.147271 Cnq = 0.000003 Cnr = -0.556732 + x force CX | CXp = -0.000000 CXq = -1.337138 CXr = 0.000000 + y force CY | CYp = -0.332918 CYq = -0.000001 CYr = 1.050216 + z force CZ | CZp = -0.000002 CZq = -31.361357 CZr = 0.000000 + x mom. Cl | Clp = -0.553742 Clq = -0.000004 Clr = 0.182717 + y mom. Cm | Cmp = -0.000003 Cmq = -89.410027 Cmr = -0.000000 + z mom. Cn | Cnp = 0.147187 Cnq = 0.000001 Cnr = -0.556761 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = 0.000071 CXd2 = -0.000525 CXd3 = -0.000000 CXd4 = -0.000179 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000401 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000669 CZd2 = -0.030463 CZd3 = 0.000000 CZd4 = -0.013982 + x force CX | CXd1 = 0.000059 CXd2 = -0.000543 CXd3 = -0.000000 CXd4 = -0.000181 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000404 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000669 CZd2 = -0.030464 CZd3 = 0.000000 CZd4 = -0.013984 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002224 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000032 Cmd2 = -0.028650 Cmd3 = 0.000000 Cmd4 = -0.068529 - z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000077 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000033 Cmd2 = -0.028648 Cmd3 = 0.000000 Cmd4 = -0.068540 + z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000081 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_02.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_02.txt index b1c7d4ee6e..4ff5bacec1 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_02.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_02.txt @@ -13,54 +13,54 @@ Run case: case_05_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = -0.00266 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.03371 - CZtot = -0.17861 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.17861 - CDtot = 0.00266 - CDvis = 0.00000 CDind = 0.0026568 - CLff = 0.17849 CDff = 0.0018435 | Trefftz - CYff = 0.00000 e = 0.5831 | Plane + CXtot = -0.00263 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.03273 + CZtot = -0.17970 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.17970 + CDtot = 0.00263 + CDvis = 0.00000 CDind = 0.00263 + CLff = 0.17954 CDff = 0.00188 | Trefftz + CYff = -0.00000 e = 0.5777 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.005314 CXv = -0.000000 CXw = 0.081408 - y force CY | CYu = -0.000000 CYv = -0.877301 CYw = -0.000000 - z force CZ | CZu = -0.357216 CZv = -0.000001 CZw = -6.659284 - x mom. Cl | Clu = -0.000000 Clv = -0.222345 Clw = -0.000006 - y mom. Cm | Cmu = -0.067419 Cmv = 0.000000 Cmw = -9.381839 - z mom. Cn | Cnu = -0.000000 Cnv = 0.307808 Cnw = -0.000000 + x force CX | CXu = -0.005255 CXv = -0.000000 CXw = 0.083915 + y force CY | CYu = -0.000000 CYv = -0.877360 CYw = -0.000000 + z force CZ | CZu = -0.359402 CZv = -0.000000 CZw = -6.660975 + x mom. Cl | Clu = -0.000000 Clv = -0.222548 Clw = -0.000001 + y mom. Cm | Cmu = -0.065451 Cmv = -0.000000 Cmw = -9.383224 + z mom. Cn | Cnu = -0.000000 Cnv = 0.307830 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = -0.253119 CXr = 0.000000 - y force CY | CYp = -0.254499 CYq = -0.000007 CYr = 1.068634 - z force CZ | CZp = -0.000011 CZq = -31.410391 CZr = 0.000001 - x mom. Cl | Clp = -0.553438 Clq = -0.000032 Clr = 0.219128 - y mom. Cm | Cmp = -0.000021 Cmq = -89.765358 Cmr = 0.000000 - z mom. Cn | Cnp = 0.096147 Cnq = 0.000003 Cnr = -0.561585 + x force CX | CXp = 0.000000 CXq = -0.254412 CXr = 0.000000 + y force CY | CYp = -0.254269 CYq = -0.000001 CYr = 1.068736 + z force CZ | CZp = -0.000002 CZq = -31.416607 CZr = 0.000000 + x mom. Cl | Clp = -0.553469 Clq = -0.000004 Clr = 0.219183 + y mom. Cm | Cmp = -0.000003 Cmq = -89.778938 Cmr = 0.000000 + z mom. Cn | Cnp = 0.096059 Cnq = 0.000000 Cnr = -0.561614 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000238 CXd2 = -0.000092 CXd3 = 0.000000 CXd4 = -0.000077 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000375 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000685 CZd2 = -0.030442 CZd3 = 0.000000 CZd4 = -0.013983 + x force CX | CXd1 = -0.000249 CXd2 = -0.000107 CXd3 = 0.000000 CXd4 = -0.000078 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000378 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000683 CZd2 = -0.030444 CZd3 = 0.000000 CZd4 = -0.013985 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002220 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000058 Cmd2 = -0.028610 Cmd3 = 0.000000 Cmd4 = -0.068591 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000040 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000058 Cmd2 = -0.028609 Cmd3 = 0.000000 Cmd4 = -0.068599 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000044 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_03.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_03.txt index bbe0fff86d..7622fbb396 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_03.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_03.txt @@ -13,54 +13,54 @@ Run case: case_05_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00611 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.36179 - CZtot = -0.41085 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.41082 - CDtot = 0.00823 - CDvis = 0.00000 CDind = 0.0082293 - CLff = 0.41037 CDff = 0.0067847 | Trefftz - CYff = -0.00000 e = 0.8375 | Plane + CXtot = 0.00625 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.36085 + CZtot = -0.41202 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.41198 + CDtot = 0.00813 + CDvis = 0.00000 CDind = 0.00813 + CLff = 0.41142 CDff = 0.00684 | Trefftz + CYff = -0.00000 e = 0.8345 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.002469 CXv = -0.000000 CXw = 0.421037 - y force CY | CYu = -0.000000 CYv = -0.884497 CYw = 0.000000 - z force CZ | CZu = -0.589404 CZv = -0.000001 CZw = -6.666610 - x mom. Cl | Clu = -0.000000 Clv = -0.250931 Clw = -0.000006 - y mom. Cm | Cmu = -0.394799 Cmv = -0.000000 Cmw = -9.427672 - z mom. Cn | Cnu = -0.000000 Cnv = 0.306098 Cnw = -0.000001 + x force CX | CXu = -0.002323 CXv = -0.000000 CXw = 0.424766 + y force CY | CYu = -0.000000 CYv = -0.884540 CYw = -0.000000 + z force CZ | CZu = -0.591648 CZv = -0.000000 CZw = -6.669003 + x mom. Cl | Clu = -0.000000 Clv = -0.251137 Clw = -0.000001 + y mom. Cm | Cmu = -0.392881 Cmv = -0.000000 Cmw = -9.429003 + z mom. Cn | Cnu = -0.000000 Cnv = 0.306119 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = 0.826439 CXr = 0.000000 - y force CY | CYp = -0.175546 CYq = -0.000006 CYr = 1.085853 - z force CZ | CZp = -0.000011 CZq = -31.427473 CZr = 0.000001 - x mom. Cl | Clp = -0.552484 Clq = -0.000033 Clr = 0.255326 - y mom. Cm | Cmp = -0.000021 Cmq = -90.029785 Cmr = 0.000002 - z mom. Cn | Cnp = 0.044906 Cnq = 0.000002 Cnr = -0.565754 + x force CX | CXp = 0.000000 CXq = 0.828622 CXr = 0.000000 + y force CY | CYp = -0.175311 CYq = -0.000001 CYr = 1.085955 + z force CZ | CZp = -0.000002 CZq = -31.433577 CZr = 0.000000 + x mom. Cl | Clp = -0.552522 Clq = -0.000004 Clr = 0.255382 + y mom. Cm | Cmp = -0.000003 Cmq = -90.038460 Cmr = 0.000000 + z mom. Cn | Cnp = 0.044815 Cnq = 0.000000 Cnr = -0.565782 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000548 CXd2 = 0.000339 CXd3 = 0.000000 CXd4 = 0.000025 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000348 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000699 CZd2 = -0.030348 CZd3 = 0.000000 CZd4 = -0.013951 + x force CX | CXd1 = -0.000559 CXd2 = 0.000327 CXd3 = 0.000000 CXd4 = 0.000024 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000352 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000696 CZd2 = -0.030350 CZd3 = 0.000000 CZd4 = -0.013952 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002211 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000084 Cmd2 = -0.028501 Cmd3 = 0.000000 Cmd4 = -0.068485 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000084 Cmd2 = -0.028500 Cmd3 = 0.000000 Cmd4 = -0.068492 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000007 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_04.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_04.txt index 59d1b1fad9..d12d1c3bcb 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_04.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_04.txt @@ -13,54 +13,54 @@ Run case: case_05_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.04140 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.85363 - CZtot = -0.75668 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.75740 - CDtot = 0.02471 - CDvis = 0.00000 CDind = 0.0247080 - CLff = 0.75716 CDff = 0.0218650 | Trefftz - CYff = -0.00000 e = 0.8847 | Plane + CXtot = 0.04178 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.85277 + CZtot = -0.75798 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.75874 + CDtot = 0.02444 + CDvis = 0.00000 CDind = 0.02444 + CLff = 0.75822 CDff = 0.02196 | Trefftz + CYff = -0.00000 e = 0.8835 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.001802 CXv = -0.000000 CXw = 0.929389 - y force CY | CYu = -0.000000 CYv = -0.893269 CYw = 0.000001 - z force CZ | CZu = -0.936252 CZv = -0.000002 CZw = -6.662368 - x mom. Cl | Clu = -0.000001 Clv = -0.293226 Clw = -0.000006 - y mom. Cm | Cmu = -0.884844 Cmv = -0.000001 Cmw = -9.474874 - z mom. Cn | Cnu = -0.000000 Cnv = 0.302835 Cnw = -0.000001 + x force CX | CXu = 0.002079 CXv = -0.000000 CXw = 0.934942 + y force CY | CYu = -0.000000 CYv = -0.893287 CYw = -0.000000 + z force CZ | CZu = -0.938577 CZv = -0.000000 CZw = -6.665809 + x mom. Cl | Clu = -0.000000 Clv = -0.293435 Clw = -0.000001 + y mom. Cm | Cmu = -0.883004 Cmv = -0.000000 Cmw = -9.476114 + z mom. Cn | Cnu = -0.000000 Cnv = 0.302855 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 2.443481 CXr = 0.000000 - y force CY | CYp = -0.056745 CYq = -0.000006 CYr = 1.109195 - z force CZ | CZp = -0.000011 CZq = -31.381304 CZr = 0.000002 - x mom. Cl | Clp = -0.549792 Clq = -0.000032 Clr = 0.309026 - y mom. Cm | Cmp = -0.000020 Cmq = -90.220665 Cmr = 0.000004 - z mom. Cn | Cnp = -0.032039 Cnq = 0.000002 Cnr = -0.570714 + x force CX | CXp = 0.000000 CXq = 2.450871 CXr = 0.000000 + y force CY | CYp = -0.056502 CYq = -0.000001 CYr = 1.109296 + z force CZ | CZp = -0.000002 CZq = -31.387234 CZr = 0.000000 + x mom. Cl | Clp = -0.549840 Clq = -0.000004 Clr = 0.309083 + y mom. Cm | Cmp = -0.000003 Cmq = -90.221992 Cmr = 0.000001 + z mom. Cn | Cnp = -0.032134 Cnq = 0.000000 Cnr = -0.570741 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001013 CXd2 = 0.000977 CXd3 = 0.000000 CXd4 = 0.000177 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000308 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000717 CZd2 = -0.030068 CZd3 = 0.000000 CZd4 = -0.013839 + x force CX | CXd1 = -0.001024 CXd2 = 0.000971 CXd3 = 0.000000 CXd4 = 0.000176 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000311 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000712 CZd2 = -0.030071 CZd3 = 0.000000 CZd4 = -0.013840 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002187 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000123 Cmd2 = -0.028208 Cmd3 = 0.000000 Cmd4 = -0.068013 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000052 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000121 Cmd2 = -0.028208 Cmd3 = 0.000000 Cmd4 = -0.068017 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_05.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_05.txt index 433e55cbf8..8bde918748 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_05.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_05.txt @@ -13,54 +13,54 @@ Run case: case_05_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.07951 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.17901 - CZtot = -0.98389 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.98625 - CDtot = 0.04099 - CDvis = 0.00000 CDind = 0.0409907 - CLff = 0.98726 CDff = 0.0369595 | Trefftz - CYff = -0.00000 e = 0.8899 | Plane + CXtot = 0.08010 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.17820 + CZtot = -0.98532 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.98774 + CDtot = 0.04058 + CDvis = 0.00000 CDind = 0.04058 + CLff = 0.98832 CDff = 0.03707 | Trefftz + CYff = -0.00000 e = 0.8891 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.004647 CXv = -0.000000 CXw = 1.266961 - y force CY | CYu = -0.000000 CYv = -0.897758 CYw = 0.000001 - z force CZ | CZu = -1.166116 CZv = -0.000002 CZw = -6.649393 - x mom. Cl | Clu = -0.000001 Clv = -0.320983 Clw = -0.000006 - y mom. Cm | Cmu = -1.210275 Cmv = -0.000001 Cmw = -9.491919 - z mom. Cn | Cnu = -0.000000 Cnv = 0.300197 Cnw = -0.000001 + x force CX | CXu = 0.005011 CXv = -0.000000 CXw = 1.273722 + y force CY | CYu = -0.000000 CYv = -0.897760 CYw = -0.000000 + z force CZ | CZu = -1.168492 CZv = -0.000000 CZw = -6.653527 + x mom. Cl | Clu = -0.000000 Clv = -0.321194 Clw = -0.000001 + y mom. Cm | Cmu = -1.208491 Cmv = -0.000000 Cmw = -9.493097 + z mom. Cn | Cnu = -0.000000 Cnv = 0.300216 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 3.518062 CXr = 0.000000 - y force CY | CYp = 0.022561 CYq = -0.000006 CYr = 1.123071 - z force CZ | CZp = -0.000010 CZq = -31.302719 CZr = 0.000003 - x mom. Cl | Clp = -0.547159 Clq = -0.000032 Clr = 0.344364 - y mom. Cm | Cmp = -0.000020 Cmq = -90.210548 Cmr = 0.000005 - z mom. Cn | Cnp = -0.083300 Cnq = 0.000002 Cnr = -0.573152 + x force CX | CXp = 0.000000 CXq = 3.528913 CXr = 0.000000 + y force CY | CYp = 0.022810 CYq = -0.000001 CYr = 1.123171 + z force CZ | CZp = -0.000002 CZq = -31.308527 CZr = 0.000000 + x mom. Cl | Clp = -0.547214 Clq = -0.000004 Clr = 0.344422 + y mom. Cm | Cmp = -0.000003 Cmq = -90.206985 Cmr = 0.000001 + z mom. Cn | Cnp = -0.083398 Cnq = 0.000000 Cnr = -0.573179 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001321 CXd2 = 0.001395 CXd3 = 0.000000 CXd4 = 0.000276 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000280 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000727 CZd2 = -0.029790 CZd3 = 0.000000 CZd4 = -0.013722 + x force CX | CXd1 = -0.001332 CXd2 = 0.001391 CXd3 = 0.000000 CXd4 = 0.000276 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000283 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000720 CZd2 = -0.029794 CZd3 = 0.000000 CZd4 = -0.013723 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002165 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000148 Cmd2 = -0.027928 Cmd3 = 0.000000 Cmd4 = -0.067493 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000088 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000146 Cmd2 = -0.027928 Cmd3 = 0.000000 Cmd4 = -0.067495 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000084 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_06.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_06.txt index 64a6ad6dbb..a1d2e0d29d 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_06.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_05_06.txt @@ -13,54 +13,54 @@ Run case: case_05_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.15809 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.65935 - CZtot = -1.31694 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = 1.32439 - CDtot = 0.07300 - CDvis = 0.00000 CDind = 0.0729982 - CLff = 1.33007 CDff = 0.0669791 | Trefftz - CYff = -0.00000 e = 0.8912 | Plane + CXtot = 0.15907 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.65861 + CZtot = -1.31860 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 1.32619 + CDtot = 0.07231 + CDvis = 0.00000 CDind = 0.07231 + CLff = 1.33112 CDff = 0.06712 | Trefftz + CYff = -0.00000 e = 0.8908 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.008903 CXv = -0.000000 CXw = 1.770296 - y force CY | CYu = -0.000000 CYv = -0.902439 CYw = 0.000002 - z force CZ | CZu = -1.508162 CZv = -0.000002 CZw = -6.614747 - x mom. Cl | Clu = -0.000001 Clv = -0.361875 Clw = -0.000006 - y mom. Cm | Cmu = -1.695534 Cmv = -0.000002 Cmw = -9.495799 - z mom. Cn | Cnu = -0.000000 Cnv = 0.295556 Cnw = -0.000001 + x force CX | CXu = 0.009397 CXv = -0.000000 CXw = 1.778853 + y force CY | CYu = -0.000000 CYv = -0.902416 CYw = 0.000000 + z force CZ | CZu = -1.510608 CZv = -0.000000 CZw = -6.619911 + x mom. Cl | Clu = -0.000000 Clv = -0.362088 Clw = -0.000001 + y mom. Cm | Cmu = -1.693837 Cmv = -0.000000 Cmw = -9.496883 + z mom. Cn | Cnu = -0.000000 Cnv = 0.295574 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000002 CXq = 5.121487 CXr = 0.000000 - y force CY | CYp = 0.141440 CYq = -0.000007 CYr = 1.141315 - z force CZ | CZp = -0.000010 CZq = -31.113380 CZr = 0.000004 - x mom. Cl | Clp = -0.541962 Clq = -0.000032 Clr = 0.396572 - y mom. Cm | Cmp = -0.000020 Cmq = -89.989342 Cmr = 0.000007 - z mom. Cn | Cnp = -0.159981 Cnq = 0.000001 Cnr = -0.575499 + x force CX | CXp = 0.000000 CXq = 5.137504 CXr = 0.000000 + y force CY | CYp = 0.141695 CYq = -0.000001 CYr = 1.141413 + z force CZ | CZp = -0.000002 CZq = -31.118986 CZr = 0.000000 + x mom. Cl | Clp = -0.542026 Clq = -0.000004 Clr = 0.396630 + y mom. Cm | Cmp = -0.000003 Cmq = -89.978432 Cmr = 0.000001 + z mom. Cn | Cnp = -0.160084 Cnq = -0.000000 Cnr = -0.575525 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001776 CXd2 = 0.002004 CXd3 = 0.000000 CXd4 = 0.000422 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000237 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000739 CZd2 = -0.029242 CZd3 = 0.000000 CZd4 = -0.013486 - x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002121 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000186 Cmd2 = -0.027383 Cmd3 = 0.000000 Cmd4 = -0.066409 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000141 Cnd4 = 0.000000 - - + x force CX | CXd1 = -0.001786 CXd2 = 0.002005 CXd3 = 0.000000 CXd4 = 0.000422 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000240 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000730 CZd2 = -0.029247 CZd3 = 0.000000 CZd4 = -0.013486 + x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002122 Cld4 = -0.000000 + y mom. Cm | Cmd1 = 0.000183 Cmd2 = -0.027384 Cmd3 = 0.000000 Cmd4 = -0.066408 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000137 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_01.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_01.txt index 8105a5c355..6dcc083293 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_01.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_01.txt @@ -13,54 +13,54 @@ Run case: case_06_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00028 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = -0.00000 Cmtot = 0.34458 - CZtot = 0.05956 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = -0.05953 - CDtot = 0.00179 - CDvis = 0.00000 CDind = 0.0017949 - CLff = -0.05953 CDff = 0.0012771 | Trefftz - CYff = -0.00000 e = 0.0937 | Plane + CXtot = 0.00021 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = -0.00000 Cmtot = 0.34617 + CZtot = 0.05825 Cntot = 0.00000 Cn'tot = 0.00000 + CLtot = -0.05822 + CDtot = 0.00182 + CDvis = 0.00000 CDind = 0.00182 + CLff = -0.05823 CDff = 0.00130 | Trefftz + CYff = -0.00000 e = 0.0879 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.009891 CXv = -0.000000 CXw = -0.299511 - y force CY | CYu = -0.000000 CYv = -0.928996 CYw = -0.000000 - z force CZ | CZu = -0.157487 CZv = -0.000001 CZw = -7.922929 - x mom. Cl | Clu = -0.000000 Clv = -0.215922 Clw = -0.000007 - y mom. Cm | Cmu = 0.303278 Cmv = 0.000003 Cmw = -11.062358 - z mom. Cn | Cnu = -0.000000 Cnv = 0.343047 Cnw = -0.000000 + x force CX | CXu = -0.010022 CXv = 0.000000 CXw = -0.299214 + y force CY | CYu = -0.000000 CYv = -0.929045 CYw = 0.000000 + z force CZ | CZu = -0.160143 CZv = -0.000000 CZw = -7.924028 + x mom. Cl | Clu = -0.000000 Clv = -0.216154 Clw = -0.000001 + y mom. Cm | Cmu = 0.306417 Cmv = 0.000001 Cmw = -11.063589 + z mom. Cn | Cnu = -0.000000 Cnv = 0.343035 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = -0.000000 CXq = -1.499537 CXr = 0.000000 - y force CY | CYp = -0.358132 CYq = -0.000002 CYr = 1.130414 - z force CZ | CZp = -0.000013 CZq = -36.884602 CZr = -0.000000 - x mom. Cl | Clp = -0.636626 Clq = -0.000040 Clr = 0.202404 - y mom. Cm | Cmp = -0.000026 Cmq =-104.222931 Cmr = -0.000004 - z mom. Cn | Cnp = 0.155554 Cnq = 0.000000 Cnr = -0.604674 + x force CX | CXp = -0.000000 CXq = -1.507574 CXr = -0.000000 + y force CY | CYp = -0.357785 CYq = -0.000000 CYr = 1.130463 + z force CZ | CZp = -0.000002 CZq = -36.890724 CZr = -0.000000 + x mom. Cl | Clp = -0.636645 Clq = -0.000005 Clr = 0.202434 + y mom. Cm | Cmp = -0.000003 Cmq =-104.242805 Cmr = -0.000001 + z mom. Cn | Cnp = 0.155385 Cnq = -0.000000 Cnr = -0.604665 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = 0.000074 CXd2 = -0.000695 CXd3 = -0.000000 CXd4 = -0.000179 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000453 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000761 CZd2 = -0.038073 CZd3 = 0.000000 CZd4 = -0.016576 + x force CX | CXd1 = 0.000061 CXd2 = -0.000719 CXd3 = -0.000000 CXd4 = -0.000182 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000457 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000762 CZd2 = -0.038073 CZd3 = 0.000000 CZd4 = -0.016580 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002586 Cld4 = -0.000000 - y mom. Cm | Cmd1 = -0.000091 Cmd2 = -0.036581 Cmd3 = 0.000000 Cmd4 = -0.082422 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000085 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = -0.000089 Cmd2 = -0.036577 Cmd3 = 0.000000 Cmd4 = -0.082438 + z mom. Cn | Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000090 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_02.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_02.txt index 9eb060f356..a53c26cf74 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_02.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_02.txt @@ -13,54 +13,54 @@ Run case: case_06_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = -0.00352 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.04266 - CZtot = -0.21751 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.21751 - CDtot = 0.00352 - CDvis = 0.00000 CDind = 0.0035209 - CLff = 0.21728 CDff = 0.0024567 | Trefftz - CYff = -0.00000 e = 0.6484 | Plane + CXtot = -0.00357 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.04109 + CZtot = -0.21886 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.21886 + CDtot = 0.00357 + CDvis = 0.00000 CDind = 0.00357 + CLff = 0.21859 CDff = 0.00251 | Trefftz + CYff = -0.00000 e = 0.6426 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.007042 CXv = -0.000000 CXw = 0.081769 - y force CY | CYu = -0.000000 CYv = -0.940388 CYw = -0.000000 - z force CZ | CZu = -0.435019 CZv = -0.000001 CZw = -7.944729 - x mom. Cl | Clu = -0.000000 Clv = -0.250944 Clw = -0.000007 - y mom. Cm | Cmu = -0.085316 Cmv = 0.000003 Cmw = -11.133167 - z mom. Cn | Cnu = -0.000000 Cnv = 0.342324 Cnw = -0.000001 + x force CX | CXu = -0.007148 CXv = -0.000000 CXw = 0.082485 + y force CY | CYu = -0.000000 CYv = -0.940431 CYw = -0.000000 + z force CZ | CZu = -0.437718 CZv = -0.000000 CZw = -7.945923 + x mom. Cl | Clu = -0.000000 Clv = -0.251177 Clw = -0.000001 + y mom. Cm | Cmu = -0.082188 Cmv = 0.000000 Cmw = -11.133526 + z mom. Cn | Cnu = -0.000000 Cnv = 0.342313 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = -0.333783 CXr = 0.000000 - y force CY | CYp = -0.268764 CYq = -0.000002 CYr = 1.154289 - z force CZ | CZp = -0.000013 CZq = -36.969437 CZr = 0.000001 - x mom. Cl | Clp = -0.636472 Clq = -0.000040 Clr = 0.247499 - y mom. Cm | Cmp = -0.000026 Cmq =-104.676361 Cmr = -0.000002 - z mom. Cn | Cnp = 0.095485 Cnq = 0.000000 Cnr = -0.611531 + x force CX | CXp = 0.000000 CXq = -0.338966 CXr = 0.000000 + y force CY | CYp = -0.268415 CYq = -0.000000 CYr = 1.154339 + z force CZ | CZp = -0.000002 CZq = -36.972527 CZr = 0.000000 + x mom. Cl | Clp = -0.636490 Clq = -0.000006 Clr = 0.247529 + y mom. Cm | Cmp = -0.000003 Cmq =-104.687897 Cmr = -0.000000 + z mom. Cn | Cnp = 0.095320 Cnq = -0.000000 Cnr = -0.611522 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000298 CXd2 = -0.000208 CXd3 = 0.000000 CXd4 = -0.000086 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000426 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000780 CZd2 = -0.038058 CZd3 = 0.000000 CZd4 = -0.016578 + x force CX | CXd1 = -0.000310 CXd2 = -0.000229 CXd3 = 0.000000 CXd4 = -0.000088 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000429 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000781 CZd2 = -0.038055 CZd3 = 0.000000 CZd4 = -0.016581 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002582 Cld4 = -0.000000 - y mom. Cm | Cmd1 = -0.000058 Cmd2 = -0.036551 Cmd3 = 0.000000 Cmd4 = -0.082483 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000046 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = -0.000056 Cmd2 = -0.036544 Cmd3 = 0.000000 Cmd4 = -0.082495 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000051 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_03.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_03.txt index 8f3af84e90..1035bc0b97 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_03.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_03.txt @@ -13,54 +13,54 @@ Run case: case_06_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00599 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.43203 - CZtot = -0.49464 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.49455 - CDtot = 0.01128 - CDvis = 0.00000 CDind = 0.0112786 - CLff = 0.49382 CDff = 0.0092730 | Trefftz - CYff = -0.00000 e = 0.8874 | Plane + CXtot = 0.00597 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.43046 + CZtot = -0.49603 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.49594 + CDtot = 0.01135 + CDvis = 0.00000 CDind = 0.01135 + CLff = 0.49513 CDff = 0.00935 | Trefftz + CYff = -0.00000 e = 0.8844 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = -0.004184 CXv = -0.000000 CXw = 0.462948 - y force CY | CYu = -0.000000 CYv = -0.950635 CYw = 0.000000 - z force CZ | CZu = -0.712021 CZv = -0.000001 CZw = -7.956851 - x mom. Cl | Clu = -0.000001 Clv = -0.285659 Clw = -0.000007 - y mom. Cm | Cmu = -0.473806 Cmv = 0.000002 Cmw = -11.190414 - z mom. Cn | Cnu = -0.000000 Cnv = 0.341185 Cnw = -0.000001 + x force CX | CXu = -0.004265 CXv = -0.000000 CXw = 0.464084 + y force CY | CYu = -0.000000 CYv = -0.950671 CYw = -0.000000 + z force CZ | CZu = -0.714760 CZv = -0.000000 CZw = -7.958138 + x mom. Cl | Clu = -0.000000 Clv = -0.285894 Clw = -0.000001 + y mom. Cm | Cmu = -0.470692 Cmv = 0.000000 Cmw = -11.189896 + z mom. Cn | Cnu = -0.000000 Cnv = 0.341174 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000000 CXq = 0.832376 CXr = 0.000000 - y force CY | CYp = -0.179070 CYq = -0.000002 CYr = 1.176759 - z force CZ | CZp = -0.000013 CZq = -37.009232 CZr = 0.000001 - x mom. Cl | Clp = -0.635542 Clq = -0.000040 Clr = 0.292294 - y mom. Cm | Cmp = -0.000026 Cmq =-105.002258 Cmr = -0.000001 - z mom. Cn | Cnp = 0.035299 Cnq = -0.000000 Cnr = -0.617642 + x force CX | CXp = 0.000000 CXq = 0.830052 CXr = 0.000000 + y force CY | CYp = -0.178718 CYq = -0.000000 CYr = 1.176809 + z force CZ | CZp = -0.000002 CZq = -37.009285 CZr = 0.000000 + x mom. Cl | Clp = -0.635559 Clq = -0.000005 Clr = 0.292324 + y mom. Cm | Cmp = -0.000003 Cmq =-105.005417 Cmr = -0.000000 + z mom. Cn | Cnp = 0.035139 Cnq = 0.000000 Cnr = -0.617634 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.000673 CXd2 = 0.000278 CXd3 = 0.000000 CXd4 = 0.000007 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000397 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000798 CZd2 = -0.037950 CZd3 = 0.000000 CZd4 = -0.016540 + x force CX | CXd1 = -0.000683 CXd2 = 0.000258 CXd3 = 0.000000 CXd4 = 0.000005 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000401 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000798 CZd2 = -0.037944 CZd3 = 0.000000 CZd4 = -0.016542 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002571 Cld4 = -0.000000 - y mom. Cm | Cmd1 = -0.000025 Cmd2 = -0.036431 Cmd3 = 0.000000 Cmd4 = -0.082343 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000008 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = -0.000023 Cmd2 = -0.036422 Cmd3 = 0.000000 Cmd4 = -0.082351 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000013 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_04.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_04.txt index 4a98069754..4d9f6ccb8f 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_04.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_04.txt @@ -13,54 +13,54 @@ Run case: case_06_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.04509 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.01593 - CZtot = -0.90750 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.90797 - CDtot = 0.03417 - CDvis = 0.00000 CDind = 0.0341712 - CLff = 0.90741 CDff = 0.0299864 | Trefftz - CYff = 0.00000 e = 0.9265 | Plane + CXtot = 0.04515 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.01431 + CZtot = -0.90895 Cntot = -0.00000 Cn'tot = -0.00000 + CLtot = 0.90943 + CDtot = 0.03424 + CDvis = 0.00000 CDind = 0.03424 + CLff = 0.90872 CDff = 0.03011 | Trefftz + CYff = 0.00000 e = 0.9255 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.000112 CXv = -0.000000 CXw = 1.033516 - y force CY | CYu = -0.000000 CYv = -0.963829 CYw = 0.000001 - z force CZ | CZu = -1.125793 CZv = -0.000002 CZw = -7.956853 - x mom. Cl | Clu = -0.000001 Clv = -0.337067 Clw = -0.000007 - y mom. Cm | Cmu = -1.055311 Cmv = 0.000001 Cmw = -11.250703 - z mom. Cn | Cnu = -0.000000 Cnv = 0.338696 Cnw = -0.000001 + x force CX | CXu = 0.000068 CXv = -0.000000 CXw = 1.035275 + y force CY | CYu = -0.000000 CYv = -0.963855 CYw = -0.000000 + z force CZ | CZu = -1.128585 CZv = -0.000000 CZw = -7.958279 + x mom. Cl | Clu = -0.000000 Clv = -0.337303 Clw = -0.000001 + y mom. Cm | Cmu = -1.052225 Cmv = 0.000000 Cmw = -11.248873 + z mom. Cn | Cnu = -0.000000 Cnv = 0.338686 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 2.579270 CXr = 0.000000 - y force CY | CYp = -0.044153 CYq = -0.000003 CYr = 1.207767 - z force CZ | CZp = -0.000013 CZq = -36.984367 CZr = 0.000002 - x mom. Cl | Clp = -0.632696 Clq = -0.000040 Clr = 0.358801 - y mom. Cm | Cmp = -0.000026 Cmq =-105.251144 Cmr = 0.000002 - z mom. Cn | Cnp = -0.055038 Cnq = -0.000001 Cnr = -0.625396 + x force CX | CXp = 0.000000 CXq = 2.581239 CXr = 0.000000 + y force CY | CYp = -0.043799 CYq = -0.000000 CYr = 1.207819 + z force CZ | CZp = -0.000002 CZq = -36.979877 CZr = 0.000000 + x mom. Cl | Clp = -0.632712 Clq = -0.000005 Clr = 0.358830 + y mom. Cm | Cmp = -0.000003 Cmq =-105.241791 Cmr = 0.000000 + z mom. Cn | Cnp = -0.055190 Cnq = -0.000000 Cnr = -0.625388 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001234 CXd2 = 0.000999 CXd3 = 0.000000 CXd4 = 0.000145 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000353 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000820 CZd2 = -0.037615 CZd3 = 0.000000 CZd4 = -0.016407 + x force CX | CXd1 = -0.001243 CXd2 = 0.000982 CXd3 = 0.000000 CXd4 = 0.000144 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000357 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000820 CZd2 = -0.037604 CZd3 = 0.000000 CZd4 = -0.016408 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002544 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000025 Cmd2 = -0.036086 Cmd3 = 0.000000 Cmd4 = -0.081756 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000049 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000027 Cmd2 = -0.036073 Cmd3 = 0.000000 Cmd4 = -0.081760 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000044 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_05.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_05.txt index 204b07b171..f1d2730edc 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_05.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_05.txt @@ -13,54 +13,54 @@ Run case: case_06_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.08754 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.40233 - CZtot = -1.17889 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.18077 - CDtot = 0.05678 - CDvis = 0.00000 CDind = 0.0567812 - CLff = 1.18182 CDff = 0.0506898 | Trefftz - CYff = 0.00000 e = 0.9298 | Plane + CXtot = 0.08767 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.40064 + CZtot = -1.18038 Cntot = -0.00000 Cn'tot = 0.00000 + CLtot = 1.18227 + CDtot = 0.05684 + CDvis = 0.00000 CDind = 0.05684 + CLff = 1.18313 CDff = 0.05084 | Trefftz + CYff = 0.00000 e = 0.9291 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.002976 CXv = -0.000000 CXw = 1.412417 - y force CY | CYu = -0.000000 CYv = -0.971159 CYw = 0.000001 - z force CZ | CZu = -1.399995 CZv = -0.000002 CZw = -7.944736 - x mom. Cl | Clu = -0.000001 Clv = -0.370834 Clw = -0.000007 - y mom. Cm | Cmu = -1.441472 Cmv = 0.000000 Cmw = -11.273769 - z mom. Cn | Cnu = -0.000000 Cnv = 0.336521 Cnw = -0.000002 + x force CX | CXu = 0.002958 CXv = -0.000000 CXw = 1.414590 + y force CY | CYu = -0.000000 CYv = -0.971179 CYw = -0.000000 + z force CZ | CZu = -1.402820 CZv = -0.000000 CZw = -7.946251 + x mom. Cl | Clu = -0.000000 Clv = -0.371071 Clw = -0.000001 + y mom. Cm | Cmu = -1.438410 Cmv = 0.000000 Cmw = -11.271067 + z mom. Cn | Cnu = -0.000000 Cnv = 0.336511 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000001 CXq = 3.740234 CXr = 0.000000 - y force CY | CYp = 0.045882 CYq = -0.000003 CYr = 1.226605 - z force CZ | CZp = -0.000013 CZq = -36.911465 CZr = 0.000003 - x mom. Cl | Clp = -0.629834 Clq = -0.000040 Clr = 0.402604 - y mom. Cm | Cmp = -0.000025 Cmq =-105.256813 Cmr = 0.000004 - z mom. Cn | Cnp = -0.115194 Cnq = -0.000001 Cnr = -0.629615 + x force CX | CXp = 0.000000 CXq = 3.745064 CXr = 0.000000 + y force CY | CYp = 0.046236 CYq = -0.000001 CYr = 1.226657 + z force CZ | CZp = -0.000002 CZq = -36.903946 CZr = 0.000000 + x mom. Cl | Clp = -0.629849 Clq = -0.000005 Clr = 0.402633 + y mom. Cm | Cmp = -0.000003 Cmq =-105.239098 Cmr = 0.000000 + z mom. Cn | Cnp = -0.115341 Cnq = 0.000000 Cnr = -0.629607 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.001606 CXd2 = 0.001471 CXd3 = 0.000000 CXd4 = 0.000236 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000323 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000833 CZd2 = -0.037278 CZd3 = 0.000000 CZd4 = -0.016269 + x force CX | CXd1 = -0.001613 CXd2 = 0.001456 CXd3 = 0.000000 CXd4 = 0.000235 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000327 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000832 CZd2 = -0.037264 CZd3 = 0.000000 CZd4 = -0.016269 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002518 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000058 Cmd2 = -0.035748 Cmd3 = 0.000000 Cmd4 = -0.081117 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000086 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000061 Cmd2 = -0.035732 Cmd3 = 0.000000 Cmd4 = -0.081118 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000082 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_06.txt b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_06.txt index 2e92734d2d..68158367b3 100644 --- a/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_06.txt +++ b/regression/scripts/AVL/avl_files/body_axis_derivatives_case_06_06.txt @@ -13,54 +13,54 @@ Run case: case_06_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.17526 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.97292 - CZtot = -1.57691 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.58338 - CDtot = 0.10123 - CDvis = 0.00000 CDind = 0.1012270 - CLff = 1.59063 CDff = 0.0918345 | Trefftz - CYff = 0.00000 e = 0.9297 | Plane + CXtot = 0.17551 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.97108 + CZtot = -1.57846 Cntot = -0.00000 Cn'tot = 0.00000 + CLtot = 1.58496 + CDtot = 0.10125 + CDvis = 0.00000 CDind = 0.10125 + CLff = 1.59194 CDff = 0.09202 | Trefftz + CYff = 0.00000 e = 0.9293 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Geometry-axis derivatives... axial vel. u sideslip vel. v normal vel. w ---------------- ---------------- ---------------- - x force CX | CXu = 0.007264 CXv = -0.000000 CXw = 1.977398 - y force CY | CYu = -0.000000 CYv = -0.979934 CYw = 0.000002 - z force CZ | CZu = -1.807998 CZv = -0.000002 CZw = -7.908420 - x mom. Cl | Clu = -0.000002 Clv = -0.420625 Clw = -0.000007 - y mom. Cm | Cmu = -2.017274 Cmv = -0.000001 Cmw = -11.282613 - z mom. Cn | Cnu = -0.000000 Cnv = 0.332491 Cnw = -0.000002 + x force CX | CXu = 0.007284 CXv = -0.000000 CXw = 1.980187 + y force CY | CYu = -0.000000 CYv = -0.979943 CYw = 0.000000 + z force CZ | CZu = -1.810863 CZv = -0.000000 CZw = -7.910066 + x mom. Cl | Clu = -0.000000 Clv = -0.420862 Clw = -0.000001 + y mom. Cm | Cmu = -2.014256 Cmv = 0.000000 Cmw = -11.278606 + z mom. Cn | Cnu = -0.000000 Cnv = 0.332482 Cnw = -0.000000 roll rate p pitch rate q yaw rate r ---------------- ---------------- ---------------- - x force CX | CXp = 0.000002 CXq = 5.472695 CXr = 0.000000 - y force CY | CYp = 0.180795 CYq = -0.000003 CYr = 1.252052 - z force CZ | CZp = -0.000013 CZq = -36.717827 CZr = 0.000004 - x mom. Cl | Clp = -0.624104 Clq = -0.000040 Clr = 0.467371 - y mom. Cm | Cmp = -0.000025 Cmq =-105.024918 Cmr = 0.000007 - z mom. Cn | Cnp = -0.205142 Cnq = -0.000001 Cnr = -0.634502 + x force CX | CXp = 0.000000 CXq = 5.481802 CXr = 0.000000 + y force CY | CYp = 0.181150 CYq = -0.000001 CYr = 1.252105 + z force CZ | CZp = -0.000002 CZq = -36.705791 CZr = 0.000000 + x mom. Cl | Clp = -0.624118 Clq = -0.000005 Clr = 0.467400 + y mom. Cm | Cmp = -0.000003 Cmq =-104.994728 Cmr = 0.000000 + z mom. Cn | Cnp = -0.205281 Cnq = 0.000000 Cnr = -0.634495 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - x force CX | CXd1 = -0.002154 CXd2 = 0.002160 CXd3 = 0.000000 CXd4 = 0.000368 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000277 CYd4 = -0.000000 - z force CZ | CZd1 = 0.000848 CZd2 = -0.036607 CZd3 = 0.000000 CZd4 = -0.015989 + x force CX | CXd1 = -0.002159 CXd2 = 0.002147 CXd3 = 0.000000 CXd4 = 0.000369 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000281 CYd4 = -0.000000 + z force CZ | CZd1 = 0.000847 CZd2 = -0.036589 CZd3 = 0.000000 CZd4 = -0.015988 x mom. Cl | Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002468 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000108 Cmd2 = -0.035081 Cmd3 = 0.000000 Cmd4 = -0.079795 - z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000141 Cnd4 = 0.000000 - - + y mom. Cm | Cmd1 = 0.000111 Cmd2 = -0.035061 Cmd3 = 0.000000 Cmd4 = -0.079791 + z mom. Cn | Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000136 Cnd4 = 0.000000 + + diff --git a/regression/scripts/AVL/avl_files/commands_01.deck b/regression/scripts/AVL/avl_files/commands_01.deck index 6523f57d6c..844d896532 100644 --- a/regression/scripts/AVL/avl_files/commands_01.deck +++ b/regression/scripts/AVL/avl_files/commands_01.deck @@ -7,6 +7,18 @@ G CASE batch_01.run OPER 1 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_01_01.txt @@ -17,6 +29,18 @@ strip_forces_case_01_01.txt sb body_axis_derivatives_case_01_01.txt 2 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_01_02.txt @@ -27,6 +51,18 @@ strip_forces_case_01_02.txt sb body_axis_derivatives_case_01_02.txt 3 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_01_03.txt @@ -37,6 +73,18 @@ strip_forces_case_01_03.txt sb body_axis_derivatives_case_01_03.txt 4 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_01_04.txt @@ -47,6 +95,18 @@ strip_forces_case_01_04.txt sb body_axis_derivatives_case_01_04.txt 5 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_01_05.txt @@ -57,6 +117,18 @@ strip_forces_case_01_05.txt sb body_axis_derivatives_case_01_05.txt 6 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_01_06.txt diff --git a/regression/scripts/AVL/avl_files/commands_02.deck b/regression/scripts/AVL/avl_files/commands_02.deck index b85cff5d06..1a9f4fadea 100644 --- a/regression/scripts/AVL/avl_files/commands_02.deck +++ b/regression/scripts/AVL/avl_files/commands_02.deck @@ -7,6 +7,18 @@ G CASE batch_02.run OPER 1 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_02_01.txt @@ -17,6 +29,18 @@ strip_forces_case_02_01.txt sb body_axis_derivatives_case_02_01.txt 2 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_02_02.txt @@ -27,6 +51,18 @@ strip_forces_case_02_02.txt sb body_axis_derivatives_case_02_02.txt 3 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_02_03.txt @@ -37,6 +73,18 @@ strip_forces_case_02_03.txt sb body_axis_derivatives_case_02_03.txt 4 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_02_04.txt @@ -47,6 +95,18 @@ strip_forces_case_02_04.txt sb body_axis_derivatives_case_02_04.txt 5 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_02_05.txt @@ -57,6 +117,18 @@ strip_forces_case_02_05.txt sb body_axis_derivatives_case_02_05.txt 6 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_02_06.txt diff --git a/regression/scripts/AVL/avl_files/commands_03.deck b/regression/scripts/AVL/avl_files/commands_03.deck index a14848336f..08012e2562 100644 --- a/regression/scripts/AVL/avl_files/commands_03.deck +++ b/regression/scripts/AVL/avl_files/commands_03.deck @@ -7,6 +7,18 @@ G CASE batch_03.run OPER 1 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_03_01.txt @@ -17,6 +29,18 @@ strip_forces_case_03_01.txt sb body_axis_derivatives_case_03_01.txt 2 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_03_02.txt @@ -27,6 +51,18 @@ strip_forces_case_03_02.txt sb body_axis_derivatives_case_03_02.txt 3 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_03_03.txt @@ -37,6 +73,18 @@ strip_forces_case_03_03.txt sb body_axis_derivatives_case_03_03.txt 4 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_03_04.txt @@ -47,6 +95,18 @@ strip_forces_case_03_04.txt sb body_axis_derivatives_case_03_04.txt 5 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_03_05.txt @@ -57,6 +117,18 @@ strip_forces_case_03_05.txt sb body_axis_derivatives_case_03_05.txt 6 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_03_06.txt diff --git a/regression/scripts/AVL/avl_files/commands_04.deck b/regression/scripts/AVL/avl_files/commands_04.deck index 758e2eb907..4b50a1281d 100644 --- a/regression/scripts/AVL/avl_files/commands_04.deck +++ b/regression/scripts/AVL/avl_files/commands_04.deck @@ -7,6 +7,18 @@ G CASE batch_04.run OPER 1 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_04_01.txt @@ -17,6 +29,18 @@ strip_forces_case_04_01.txt sb body_axis_derivatives_case_04_01.txt 2 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_04_02.txt @@ -27,6 +51,18 @@ strip_forces_case_04_02.txt sb body_axis_derivatives_case_04_02.txt 3 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_04_03.txt @@ -37,6 +73,18 @@ strip_forces_case_04_03.txt sb body_axis_derivatives_case_04_03.txt 4 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_04_04.txt @@ -47,6 +95,18 @@ strip_forces_case_04_04.txt sb body_axis_derivatives_case_04_04.txt 5 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_04_05.txt @@ -57,6 +117,18 @@ strip_forces_case_04_05.txt sb body_axis_derivatives_case_04_05.txt 6 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_04_06.txt diff --git a/regression/scripts/AVL/avl_files/commands_05.deck b/regression/scripts/AVL/avl_files/commands_05.deck index 0d0564edff..62e5864496 100644 --- a/regression/scripts/AVL/avl_files/commands_05.deck +++ b/regression/scripts/AVL/avl_files/commands_05.deck @@ -7,6 +7,18 @@ G CASE batch_05.run OPER 1 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_05_01.txt @@ -17,6 +29,18 @@ strip_forces_case_05_01.txt sb body_axis_derivatives_case_05_01.txt 2 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_05_02.txt @@ -27,6 +51,18 @@ strip_forces_case_05_02.txt sb body_axis_derivatives_case_05_02.txt 3 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_05_03.txt @@ -37,6 +73,18 @@ strip_forces_case_05_03.txt sb body_axis_derivatives_case_05_03.txt 4 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_05_04.txt @@ -47,6 +95,18 @@ strip_forces_case_05_04.txt sb body_axis_derivatives_case_05_04.txt 5 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_05_05.txt @@ -57,6 +117,18 @@ strip_forces_case_05_05.txt sb body_axis_derivatives_case_05_05.txt 6 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_05_06.txt diff --git a/regression/scripts/AVL/avl_files/commands_06.deck b/regression/scripts/AVL/avl_files/commands_06.deck index edc269c82f..a9de4a6e7a 100644 --- a/regression/scripts/AVL/avl_files/commands_06.deck +++ b/regression/scripts/AVL/avl_files/commands_06.deck @@ -7,6 +7,18 @@ G CASE batch_06.run OPER 1 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_06_01.txt @@ -17,6 +29,18 @@ strip_forces_case_06_01.txt sb body_axis_derivatives_case_06_01.txt 2 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_06_02.txt @@ -27,6 +51,18 @@ strip_forces_case_06_02.txt sb body_axis_derivatives_case_06_02.txt 3 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_06_03.txt @@ -37,6 +73,18 @@ strip_forces_case_06_03.txt sb body_axis_derivatives_case_06_03.txt 4 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_06_04.txt @@ -47,6 +95,18 @@ strip_forces_case_06_04.txt sb body_axis_derivatives_case_06_04.txt 5 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_06_05.txt @@ -57,6 +117,18 @@ strip_forces_case_06_05.txt sb body_axis_derivatives_case_06_05.txt 6 +D1 +D1 +0.0 +D2 +D2 +0.0 +D3 +D3 +0.0 +D4 +D4 +0.0 x st stability_axis_derivatives_case_06_06.txt diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_01.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_01.txt index f32d5efb19..c0e448e588 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_01.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_01.txt @@ -13,57 +13,57 @@ Run case: case_01_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00049 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.25003 - CZtot = 0.04804 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = -0.04803 - CDtot = 0.00119 - CDvis = 0.00000 CDind = 0.0011874 - CLff = -0.04796 CDff = 0.0008417 | Trefftz - CYff = 0.00000 e = 0.0922 | Plane - + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00047 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.25074 + CZtot = 0.04717 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = -0.04716 + CDtot = 0.00118 + CDvis = 0.00000 CDind = 0.00118 + CLff = -0.04708 CDff = 0.00086 | Trefftz + CYff = 0.00000 e = 0.0873 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.675554 CLb = 0.000001 - y force CY | CYa = -0.000001 CYb = -0.813809 - x' mom. Cl'| Cla = -0.000004 Clb = -0.183377 - y mom. Cm | Cma = -7.953726 Cmb = -0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.271950 + z' force CL | CLa = 5.675841 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.813886 + x' mom. Cl'| Cla = -0.000001 Clb = -0.183550 + y mom. Cm | Cma = -7.954853 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.271978 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.133717 CLr = -0.000000 - y force CY | CYp = -0.343454 CYq = -0.000008 CYr = 0.965809 - x' mom. Cl'| Clp = -0.495295 Clq = -0.000023 Clr = 0.165910 - y mom. Cm | Cmp = -0.000016 Cmq = -77.724060 Cmr = 0.000000 - z' mom. Cn'| Cnp = 0.139193 Cnq = 0.000003 Cnr = -0.502713 + z' force CL | CLp = 0.000001 CLq = 27.138607 CLr = -0.000000 + y force CY | CYp = -0.343244 CYq = -0.000001 CYr = 0.965939 + x' mom. Cl'| Clp = -0.495306 Clq = -0.000003 Clr = 0.165973 + y mom. Cm | Cmp = -0.000002 Cmq = -77.741516 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.139133 Cnq = 0.000001 Cnr = -0.502758 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000585 CLd2 = 0.025135 CLd3 = -0.000000 CLd4 = 0.012030 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000359 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000585 CLd2 = 0.025135 CLd3 = -0.000000 CLd4 = 0.012032 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000361 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001927 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000088 Cmd2 = -0.023284 Cmd3 = 0.000000 Cmd4 = -0.058272 - z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000072 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000122 CDffd3 = 0.000000 CDffd4 = -0.000163 - span eff. | ed1 = 0.002010 ed2 = -0.083242 ed3 = 0.000000 ed4 = -0.028303 - - + y mom. Cm | Cmd1 = 0.000089 Cmd2 = -0.023281 Cmd3 = 0.000000 Cmd4 = -0.058282 + z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000075 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000123 CDffd3 = 0.000000 CDffd4 = -0.000162 + span eff. | ed1 = 0.001949 ed2 = -0.080704 ed3 = 0.000000 ed4 = -0.028023 + + - Neutral point Xnp = 21.244812 + Neutral point Xnp = 21.245352 - Clb Cnr / Clr Cnb = 2.043154 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 2.044292 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_02.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_02.txt index 04b81a9b28..b397fe97a6 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_02.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_02.txt @@ -13,57 +13,57 @@ Run case: case_01_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = -0.00210 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.02877 - CZtot = -0.15023 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.15023 - CDtot = 0.00210 - CDvis = 0.00000 CDind = 0.0020971 - CLff = 0.15019 CDff = 0.0014556 | Trefftz - CYff = 0.00000 e = 0.5229 | Plane - + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = -0.00202 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.02810 + CZtot = -0.15111 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.15111 + CDtot = 0.00202 + CDvis = 0.00000 CDind = 0.00202 + CLff = 0.15108 CDff = 0.00149 | Trefftz + CYff = 0.00000 e = 0.5181 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.681139 CLb = 0.000001 - y force CY | CYa = -0.000000 CYb = -0.819873 - x' mom. Cl'| Cla = -0.000004 Clb = -0.197950 - y mom. Cm | Cma = -8.014050 Cmb = -0.000002 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.276472 + z' force CL | CLa = 5.681394 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.819924 + x' mom. Cl'| Cla = -0.000001 Clb = -0.198123 + y mom. Cm | Cma = -8.014884 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.276504 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.145086 CLr = -0.000001 - y force CY | CYp = -0.239545 CYq = -0.000007 CYr = 0.991879 - x' mom. Cl'| Clp = -0.484302 Clq = -0.000023 Clr = 0.195371 - y mom. Cm | Cmp = -0.000016 Cmq = -78.041107 Cmr = 0.000002 - z' mom. Cn'| Cnp = 0.094390 Cnq = 0.000003 Cnr = -0.516802 + z' force CL | CLp = 0.000001 CLq = 27.149084 CLr = -0.000000 + y force CY | CYp = -0.239303 CYq = -0.000001 CYr = 0.991999 + x' mom. Cl'| Clp = -0.484317 Clq = -0.000003 Clr = 0.195433 + y mom. Cm | Cmp = -0.000002 Cmq = -78.053085 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.094324 Cnq = 0.000000 Cnr = -0.516846 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000596 CLd2 = 0.025113 CLd3 = -0.000000 CLd4 = 0.012032 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000335 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000596 CLd2 = 0.025113 CLd3 = -0.000000 CLd4 = 0.012034 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000338 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001924 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000110 Cmd2 = -0.023241 Cmd3 = 0.000000 Cmd4 = -0.058332 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000004 CDffd2 = 0.000146 CDffd3 = -0.000000 CDffd4 = 0.000104 - span eff. | ed1 = -0.002539 ed2 = 0.122076 ed3 = -0.000000 ed4 = 0.046069 - - + y mom. Cm | Cmd1 = 0.000110 Cmd2 = -0.023240 Cmd3 = 0.000000 Cmd4 = -0.058340 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000041 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000004 CDffd2 = 0.000146 CDffd3 = -0.000000 CDffd4 = 0.000105 + span eff. | ed1 = -0.002522 ed2 = 0.121264 ed3 = -0.000000 ed4 = 0.045558 + + - Neutral point Xnp = 21.283945 + Neutral point Xnp = 21.284298 - Clb Cnr / Clr Cnb = 1.893944 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.894947 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_03.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_03.txt index ed43f88889..805e4a3905 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_03.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_03.txt @@ -13,57 +13,57 @@ Run case: case_01_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00590 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.30900 - CZtot = -0.34840 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.34839 - CDtot = 0.00626 - CDvis = 0.00000 CDind = 0.0062649 - CLff = 0.34816 CDff = 0.0052006 | Trefftz - CYff = 0.00000 e = 0.7865 | Plane - + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00613 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.30835 + CZtot = -0.34929 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.34929 + CDtot = 0.00606 + CDvis = 0.00000 CDind = 0.00606 + CLff = 0.34905 CDff = 0.00525 | Trefftz + CYff = 0.00000 e = 0.7834 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.670020 CLb = 0.000002 - y force CY | CYa = 0.000000 CYb = -0.824938 - x' mom. Cl'| Cla = -0.000004 Clb = -0.212172 - y mom. Cm | Cma = -8.035330 Cmb = -0.000002 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.281999 + z' force CL | CLa = 5.670436 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.824962 + x' mom. Cl'| Cla = -0.000001 Clb = -0.212345 + y mom. Cm | Cma = -8.035870 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.282036 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.159395 CLr = -0.000002 - y force CY | CYp = -0.134072 CYq = -0.000006 CYr = 1.010638 - x' mom. Cl'| Clp = -0.473794 Clq = -0.000023 Clr = 0.223624 - y mom. Cm | Cmp = -0.000016 Cmq = -78.263054 Cmr = 0.000004 - z' mom. Cn'| Cnp = 0.048502 Cnq = 0.000004 Cnr = -0.529187 + z' force CL | CLp = 0.000001 CLq = 27.162777 CLr = -0.000000 + y force CY | CYp = -0.133797 CYq = -0.000000 CYr = 1.010745 + x' mom. Cl'| Clp = -0.473812 Clq = -0.000003 Clr = 0.223685 + y mom. Cm | Cmp = -0.000002 Cmq = -78.269577 Cmr = 0.000001 + z' mom. Cn'| Cnp = 0.048430 Cnq = 0.000000 Cnr = -0.529230 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000623 CLd2 = 0.025026 CLd3 = -0.000000 CLd4 = 0.011998 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000311 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000623 CLd2 = 0.025026 CLd3 = -0.000000 CLd4 = 0.011999 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000314 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001916 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000131 Cmd2 = -0.023143 Cmd3 = 0.000000 Cmd4 = -0.058250 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000414 CDffd3 = -0.000000 CDffd4 = 0.000370 - span eff. | ed1 = -0.001019 ed2 = 0.050492 ed3 = 0.000000 ed4 = -0.001902 - - + y mom. Cm | Cmd1 = 0.000131 Cmd2 = -0.023142 Cmd3 = 0.000000 Cmd4 = -0.058256 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000007 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000413 CDffd3 = -0.000000 CDffd4 = 0.000371 + span eff. | ed1 = -0.001021 ed2 = 0.050667 ed3 = 0.000000 ed4 = -0.001695 + + - Neutral point Xnp = 21.311554 + Neutral point Xnp = 21.311516 - Clb Cnr / Clr Cnb = 1.780456 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.781335 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_04.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_04.txt index 014d966f1c..9d1bbdfd61 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_04.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_04.txt @@ -13,57 +13,57 @@ Run case: case_01_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.03763 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.72902 - CZtot = -0.64335 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.64418 - CDtot = 0.01858 - CDvis = 0.00000 CDind = 0.0185847 - CLff = 0.64424 CDff = 0.0166451 | Trefftz - CYff = -0.00000 e = 0.8414 | Plane - + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.03822 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -0.72840 + CZtot = -0.64423 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.64511 + CDtot = 0.01807 + CDvis = 0.00000 CDind = 0.01807 + CLff = 0.64513 CDff = 0.01672 | Trefftz + CYff = -0.00000 e = 0.8401 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.622144 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.830650 - x' mom. Cl'| Cla = -0.000004 Clb = -0.232696 - y mom. Cm | Cma = -7.993866 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.292116 + z' force CL | CLa = 5.623157 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.830633 + x' mom. Cl'| Cla = -0.000001 Clb = -0.232869 + y mom. Cm | Cma = -7.993962 Cmb = -0.000001 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.292159 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.186218 CLr = -0.000003 - y force CY | CYp = 0.025948 CYq = -0.000006 CYr = 1.024876 - x' mom. Cl'| Clp = -0.459171 Clq = -0.000023 Clr = 0.263921 - y mom. Cm | Cmp = -0.000015 Cmq = -78.417145 Cmr = 0.000006 - z' mom. Cn'| Cnp = -0.021983 Cnq = 0.000004 Cnr = -0.544334 + z' force CL | CLp = 0.000001 CLq = 27.189186 CLr = -0.000000 + y force CY | CYp = 0.026270 CYq = -0.000001 CYr = 1.024961 + x' mom. Cl'| Clp = -0.459196 Clq = -0.000003 Clr = 0.263983 + y mom. Cm | Cmp = -0.000002 Cmq = -78.415459 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.022062 Cnq = 0.000001 Cnr = -0.544374 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000694 CLd2 = 0.024775 CLd3 = -0.000000 CLd4 = 0.011879 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000273 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000693 CLd2 = 0.024776 CLd3 = -0.000000 CLd4 = 0.011879 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000276 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001895 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000162 Cmd2 = -0.022890 Cmd3 = 0.000000 Cmd4 = -0.057861 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000021 CDffd2 = 0.000809 CDffd3 = -0.000000 CDffd4 = 0.000763 - span eff. | ed1 = -0.000496 ed2 = 0.024059 ed3 = 0.000000 ed4 = -0.007533 - - + y mom. Cm | Cmd1 = 0.000162 Cmd2 = -0.022890 Cmd3 = 0.000000 Cmd4 = -0.057863 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000044 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000021 CDffd2 = 0.000808 CDffd3 = -0.000000 CDffd4 = 0.000764 + span eff. | ed1 = -0.000497 ed2 = 0.024141 ed3 = 0.000000 ed4 = -0.007455 + + - Neutral point Xnp = 21.331429 + Neutral point Xnp = 21.330418 - Clb Cnr / Clr Cnb = 1.642949 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.643666 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_05.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_05.txt index 50bdff1dda..d652934a1d 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_05.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_05.txt @@ -13,57 +13,57 @@ Run case: case_01_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.07180 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.00684 - CZtot = -0.83705 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.83957 - CDtot = 0.03075 - CDvis = 0.00000 CDind = 0.0307508 - CLff = 0.84069 CDff = 0.0281052 | Trefftz - CYff = -0.00000 e = 0.8485 | Plane - + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.07271 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -1.00621 + CZtot = -0.83793 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.84054 + CDtot = 0.02995 + CDvis = 0.00000 CDind = 0.02995 + CLff = 0.84158 CDff = 0.02819 | Trefftz + CYff = -0.00000 e = 0.8477 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.569717 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.833194 - x' mom. Cl'| Cla = -0.000004 Clb = -0.245742 - y mom. Cm | Cma = -7.917500 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.300029 + z' force CL | CLa = 5.571357 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.833150 + x' mom. Cl'| Cla = -0.000001 Clb = -0.245914 + y mom. Cm | Cma = -7.917298 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.300076 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.207537 CLr = -0.000004 - y force CY | CYp = 0.133077 CYq = -0.000005 CYr = 1.025035 - x' mom. Cl'| Clp = -0.450316 Clq = -0.000023 Clr = 0.289540 - y mom. Cm | Cmp = -0.000015 Cmq = -78.400467 Cmr = 0.000008 - z' mom. Cn'| Cnp = -0.069803 Cnq = 0.000004 Cnr = -0.552010 + z' force CL | CLp = 0.000001 CLq = 27.210587 CLr = -0.000000 + y force CY | CYp = 0.133429 CYq = -0.000001 CYr = 1.025101 + x' mom. Cl'| Clp = -0.450346 Clq = -0.000003 Clr = 0.289602 + y mom. Cm | Cmp = -0.000002 Cmq = -78.393318 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.069886 Cnq = 0.000001 Cnr = -0.552047 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000761 CLd2 = 0.024529 CLd3 = -0.000000 CLd4 = 0.011755 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000248 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000760 CLd2 = 0.024530 CLd3 = -0.000000 CLd4 = 0.011755 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000250 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001875 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000182 Cmd2 = -0.022653 Cmd3 = 0.000000 Cmd4 = -0.057426 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000081 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000027 CDffd2 = 0.001066 CDffd3 = -0.000000 CDffd4 = 0.001020 - span eff. | ed1 = -0.000370 ed2 = 0.017696 ed3 = 0.000000 ed4 = -0.006940 - - + y mom. Cm | Cmd1 = 0.000182 Cmd2 = -0.022654 Cmd3 = 0.000000 Cmd4 = -0.057426 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000078 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000027 CDffd2 = 0.001066 CDffd3 = -0.000000 CDffd4 = 0.001021 + span eff. | ed1 = -0.000371 ed2 = 0.017745 ed3 = 0.000000 ed4 = -0.006896 + + - Neutral point Xnp = 21.330042 + Neutral point Xnp = 21.328117 - Clb Cnr / Clr Cnb = 1.561546 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.562165 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_06.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_06.txt index 154d6b777a..27bddbc91b 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_06.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_01_06.txt @@ -13,57 +13,57 @@ Run case: case_01_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.050 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.14214 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.41689 - CZtot = -1.12085 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.12851 - CDtot = 0.05465 - CDvis = 0.00000 CDind = 0.0546506 - CLff = 1.13338 CDff = 0.0509013 | Trefftz - CYff = -0.00000 e = 0.8516 | Plane - + Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.14365 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -1.41624 + CZtot = -1.12170 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 1.12960 + CDtot = 0.05332 + CDvis = 0.00000 CDind = 0.05332 + CLff = 1.13427 CDff = 0.05101 | Trefftz + CYff = -0.00000 e = 0.8510 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.461201 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.835105 - x' mom. Cl'| Cla = -0.000004 Clb = -0.264198 - y mom. Cm | Cma = -7.730793 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.313556 + z' force CL | CLa = 5.464103 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.835022 + x' mom. Cl'| Cla = -0.000001 Clb = -0.264368 + y mom. Cm | Cma = -7.730145 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.313609 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.244431 CLr = -0.000005 - y force CY | CYp = 0.293139 CYq = -0.000003 CYr = 1.011270 - x' mom. Cl'| Clp = -0.438554 Clq = -0.000023 Clr = 0.326365 - y mom. Cm | Cmp = -0.000014 Cmq = -78.196381 Cmr = 0.000010 - z' mom. Cn'| Cnp = -0.142287 Cnq = 0.000004 Cnr = -0.559714 + z' force CL | CLp = 0.000001 CLq = 27.248106 CLr = -0.000001 + y force CY | CYp = 0.293532 CYq = -0.000000 CYr = 1.011305 + x' mom. Cl'| Clp = -0.438591 Clq = -0.000003 Clr = 0.326427 + y mom. Cm | Cmp = -0.000001 Cmq = -78.181023 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.142376 Cnq = 0.000000 Cnr = -0.559748 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000889 CLd2 = 0.024045 CLd3 = -0.000000 CLd4 = 0.011505 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000209 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000887 CLd2 = 0.024048 CLd3 = -0.000000 CLd4 = 0.011504 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000212 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001838 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000212 Cmd2 = -0.022196 Cmd3 = 0.000000 Cmd4 = -0.056516 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000130 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000036 CDffd2 = 0.001441 CDffd3 = -0.000000 CDffd4 = 0.001394 - span eff. | ed1 = -0.000269 ed2 = 0.012613 ed3 = 0.000000 ed4 = -0.005757 - - + y mom. Cm | Cmd1 = 0.000211 Cmd2 = -0.022198 Cmd3 = 0.000000 Cmd4 = -0.056512 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000127 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000036 CDffd2 = 0.001441 CDffd3 = -0.000000 CDffd4 = 0.001395 + span eff. | ed1 = -0.000269 ed2 = 0.012640 ed3 = 0.000000 ed4 = -0.005735 + + - Neutral point Xnp = 21.304880 + Neutral point Xnp = 21.301193 - Clb Cnr / Clr Cnb = 1.445032 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.445525 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_01.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_01.txt index d292bb8abe..67c7d012e7 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_01.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_01.txt @@ -13,57 +13,57 @@ Run case: case_02_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00049 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.25163 - CZtot = 0.04827 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = -0.04825 - CDtot = 0.00119 - CDvis = 0.00000 CDind = 0.0011936 - CLff = -0.04819 CDff = 0.0008482 | Trefftz - CYff = 0.00000 e = 0.0924 | Plane - + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00046 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.25235 + CZtot = 0.04739 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = -0.04738 + CDtot = 0.00120 + CDvis = 0.00000 CDind = 0.00120 + CLff = -0.04730 CDff = 0.00086 | Trefftz + CYff = 0.00000 e = 0.0875 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.711009 CLb = 0.000001 - y force CY | CYa = -0.000001 CYb = -0.815999 - x' mom. Cl'| Cla = -0.000004 Clb = -0.184183 - y mom. Cm | Cma = -8.003715 Cmb = -0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.273145 + z' force CL | CLa = 5.710956 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.816079 + x' mom. Cl'| Cla = -0.000001 Clb = -0.184355 + y mom. Cm | Cma = -8.004801 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.273173 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.289513 CLr = -0.000000 - y force CY | CYp = -0.344506 CYq = -0.000007 CYr = 0.968652 - x' mom. Cl'| Clp = -0.497946 Clq = -0.000023 Clr = 0.166554 - y mom. Cm | Cmp = -0.000016 Cmq = -78.154465 Cmr = 0.000000 - z' mom. Cn'| Cnp = 0.139526 Cnq = 0.000003 Cnr = -0.504389 + z' force CL | CLp = 0.000001 CLq = 27.294111 CLr = -0.000000 + y force CY | CYp = -0.344291 CYq = -0.000001 CYr = 0.968781 + x' mom. Cl'| Clp = -0.497951 Clq = -0.000003 Clr = 0.166616 + y mom. Cm | Cmp = -0.000002 Cmq = -78.173744 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.139463 Cnq = 0.000000 Cnr = -0.504434 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000588 CLd2 = 0.025324 CLd3 = -0.000000 CLd4 = 0.012101 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000360 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000588 CLd2 = 0.025323 CLd3 = -0.000000 CLd4 = 0.012103 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000363 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001938 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000087 Cmd2 = -0.023471 Cmd3 = 0.000000 Cmd4 = -0.058644 - z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000072 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000123 CDffd3 = 0.000000 CDffd4 = -0.000165 - span eff. | ed1 = 0.002017 ed2 = -0.083666 ed3 = 0.000000 ed4 = -0.028297 - - + y mom. Cm | Cmd1 = 0.000088 Cmd2 = -0.023468 Cmd3 = 0.000000 Cmd4 = -0.058654 + z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000076 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000124 CDffd3 = 0.000000 CDffd4 = -0.000164 + span eff. | ed1 = 0.001955 ed2 = -0.081109 ed3 = 0.000000 ed4 = -0.028022 + + - Neutral point Xnp = 21.245035 + Neutral point Xnp = 21.245895 - Clb Cnr / Clr Cnb = 2.042045 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 2.043177 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_02.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_02.txt index 78fdad3807..5a0a485d08 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_02.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_02.txt @@ -13,57 +13,57 @@ Run case: case_02_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = -0.00211 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.02893 - CZtot = -0.15125 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.15125 - CDtot = 0.00211 - CDvis = 0.00000 CDind = 0.0021079 - CLff = 0.15120 CDff = 0.0014688 | Trefftz - CYff = 0.00000 e = 0.5252 | Plane - + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = -0.00207 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = 0.00000 Cmtot = -0.02823 + CZtot = -0.15211 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.15211 + CDtot = 0.00207 + CDvis = 0.00000 CDind = 0.00207 + CLff = 0.15210 CDff = 0.00150 | Trefftz + CYff = 0.00000 e = 0.5204 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.716895 CLb = 0.000001 - y force CY | CYa = -0.000000 CYb = -0.822140 - x' mom. Cl'| Cla = -0.000004 Clb = -0.198885 - y mom. Cm | Cma = -8.064782 Cmb = -0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.277708 + z' force CL | CLa = 5.716141 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.822199 + x' mom. Cl'| Cla = -0.000001 Clb = -0.199055 + y mom. Cm | Cma = -8.065081 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.277739 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.302330 CLr = -0.000001 - y force CY | CYp = -0.240175 CYq = -0.000006 CYr = 0.994895 - x' mom. Cl'| Clp = -0.486926 Clq = -0.000023 Clr = 0.196278 - y mom. Cm | Cmp = -0.000015 Cmq = -78.475784 Cmr = 0.000002 - z' mom. Cn'| Cnp = 0.094500 Cnq = 0.000003 Cnr = -0.518562 + z' force CL | CLp = 0.000001 CLq = 27.304304 CLr = -0.000000 + y force CY | CYp = -0.239931 CYq = -0.000001 CYr = 0.995013 + x' mom. Cl'| Clp = -0.486923 Clq = -0.000003 Clr = 0.196337 + y mom. Cm | Cmp = -0.000002 Cmq = -78.487526 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.094433 Cnq = 0.000000 Cnr = -0.518606 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000599 CLd2 = 0.025302 CLd3 = -0.000000 CLd4 = 0.012104 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000337 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000599 CLd2 = 0.025301 CLd3 = -0.000000 CLd4 = 0.012105 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000339 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001935 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000108 Cmd2 = -0.023429 Cmd3 = 0.000000 Cmd4 = -0.058705 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000004 CDffd2 = 0.000150 CDffd3 = -0.000000 CDffd4 = 0.000105 - span eff. | ed1 = -0.002532 ed2 = 0.122070 ed3 = -0.000000 ed4 = 0.046340 - - + y mom. Cm | Cmd1 = 0.000109 Cmd2 = -0.023427 Cmd3 = 0.000000 Cmd4 = -0.058713 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000041 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000004 CDffd2 = 0.000149 CDffd3 = -0.000000 CDffd4 = 0.000106 + span eff. | ed1 = -0.002515 ed2 = 0.121270 ed3 = 0.000000 ed4 = 0.045824 + + - Neutral point Xnp = 21.284163 + Neutral point Xnp = 21.285172 - Clb Cnr / Clr Cnb = 1.892102 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.893086 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_03.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_03.txt index c1a253be84..55b2e98e06 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_03.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_03.txt @@ -13,57 +13,57 @@ Run case: case_02_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00593 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.31094 - CZtot = -0.35067 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.35067 - CDtot = 0.00631 - CDvis = 0.00000 CDind = 0.0063121 - CLff = 0.35041 CDff = 0.0052544 | Trefftz - CYff = 0.00000 e = 0.7885 | Plane - + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00609 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.31024 + CZtot = -0.35149 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.35149 + CDtot = 0.00618 + CDvis = 0.00000 CDind = 0.00618 + CLff = 0.35131 CDff = 0.00530 | Trefftz + CYff = 0.00000 e = 0.7855 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.705938 CLb = 0.000001 - y force CY | CYa = 0.000000 CYb = -0.827280 - x' mom. Cl'| Cla = -0.000004 Clb = -0.213234 - y mom. Cm | Cma = -8.086563 Cmb = -0.000002 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.283285 + z' force CL | CLa = 5.704628 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.827316 + x' mom. Cl'| Cla = -0.000001 Clb = -0.213400 + y mom. Cm | Cma = -8.086069 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.283320 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.317999 CLr = -0.000002 - y force CY | CYp = -0.134268 CYq = -0.000006 CYr = 1.013796 - x' mom. Cl'| Clp = -0.476387 Clq = -0.000023 Clr = 0.224787 - y mom. Cm | Cmp = -0.000015 Cmq = -78.701515 Cmr = 0.000004 - z' mom. Cn'| Cnp = 0.048384 Cnq = 0.000003 Cnr = -0.531030 + z' force CL | CLp = 0.000001 CLq = 27.317526 CLr = -0.000000 + y force CY | CYp = -0.133995 CYq = -0.000001 CYr = 1.013902 + x' mom. Cl'| Clp = -0.476375 Clq = -0.000003 Clr = 0.224843 + y mom. Cm | Cmp = -0.000002 Cmq = -78.705673 Cmr = 0.000001 + z' mom. Cn'| Cnp = 0.048312 Cnq = 0.000000 Cnr = -0.531072 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000626 CLd2 = 0.025215 CLd3 = -0.000000 CLd4 = 0.012070 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000312 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000627 CLd2 = 0.025213 CLd3 = -0.000000 CLd4 = 0.012071 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000315 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001927 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000129 Cmd2 = -0.023331 Cmd3 = 0.000000 Cmd4 = -0.058622 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000421 CDffd3 = -0.000000 CDffd4 = 0.000373 - span eff. | ed1 = -0.001011 ed2 = 0.050294 ed3 = 0.000000 ed4 = -0.001874 - - + y mom. Cm | Cmd1 = 0.000130 Cmd2 = -0.023328 Cmd3 = 0.000000 Cmd4 = -0.058628 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000007 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000420 CDffd3 = -0.000000 CDffd4 = 0.000374 + span eff. | ed1 = -0.001013 ed2 = 0.050473 ed3 = 0.000000 ed4 = -0.001667 + + - Neutral point Xnp = 21.311800 + Neutral point Xnp = 21.312811 - Clb Cnr / Clr Cnb = 1.778205 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.779063 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_04.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_04.txt index c30b50cfd9..a37ffaf8c4 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_04.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_04.txt @@ -13,57 +13,57 @@ Run case: case_02_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.03783 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.73366 - CZtot = -0.64750 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.64834 - CDtot = 0.01875 - CDvis = 0.00000 CDind = 0.0187475 - CLff = 0.64835 CDff = 0.0168225 | Trefftz - CYff = -0.00000 e = 0.8432 | Plane - + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.03825 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.73290 + CZtot = -0.64821 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.64908 + CDtot = 0.01839 + CDvis = 0.00000 CDind = 0.01839 + CLff = 0.64924 CDff = 0.01689 | Trefftz + CYff = -0.00000 e = 0.8419 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.658041 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.833099 - x' mom. Cl'| Cla = -0.000004 Clb = -0.233940 - y mom. Cm | Cma = -8.045383 Cmb = -0.000002 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.293491 + z' force CL | CLa = 5.656183 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.833101 + x' mom. Cl'| Cla = -0.000001 Clb = -0.234101 + y mom. Cm | Cma = -8.043707 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.293532 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.346661 CLr = -0.000003 - y force CY | CYp = 0.026418 CYq = -0.000005 CYr = 1.028191 - x' mom. Cl'| Clp = -0.461713 Clq = -0.000022 Clr = 0.265456 - y mom. Cm | Cmp = -0.000015 Cmq = -78.860260 Cmr = 0.000006 - z' mom. Cn'| Cnp = -0.022452 Cnq = 0.000004 Cnr = -0.546296 + z' force CL | CLp = 0.000001 CLq = 27.342909 CLr = -0.000000 + y force CY | CYp = 0.026733 CYq = -0.000001 CYr = 1.028273 + x' mom. Cl'| Clp = -0.461689 Clq = -0.000003 Clr = 0.265508 + y mom. Cm | Cmp = -0.000002 Cmq = -78.853050 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.022532 Cnq = 0.000000 Cnr = -0.546334 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000697 CLd2 = 0.024964 CLd3 = -0.000000 CLd4 = 0.011950 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000275 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000698 CLd2 = 0.024959 CLd3 = -0.000000 CLd4 = 0.011950 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000277 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001906 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000160 Cmd2 = -0.023077 Cmd3 = 0.000000 Cmd4 = -0.058231 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000021 CDffd2 = 0.000822 CDffd3 = -0.000000 CDffd4 = 0.000771 - span eff. | ed1 = -0.000492 ed2 = 0.023954 ed3 = 0.000000 ed4 = -0.007536 - - + y mom. Cm | Cmd1 = 0.000162 Cmd2 = -0.023075 Cmd3 = 0.000000 Cmd4 = -0.058233 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000045 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000021 CDffd2 = 0.000821 CDffd3 = -0.000000 CDffd4 = 0.000772 + span eff. | ed1 = -0.000493 ed2 = 0.024036 ed3 = 0.000000 ed4 = -0.007458 + + - Neutral point Xnp = 21.331787 + Neutral point Xnp = 21.332508 - Clb Cnr / Clr Cnb = 1.640378 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.641080 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_05.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_05.txt index 7b567e4333..843bf58cb1 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_05.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_05.txt @@ -13,57 +13,57 @@ Run case: case_02_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.07218 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.01328 - CZtot = -0.84245 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.84497 - CDtot = 0.03103 - CDvis = 0.00000 CDind = 0.0310320 - CLff = 0.84603 CDff = 0.0284063 | Trefftz - CYff = -0.00000 e = 0.8503 | Plane - + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.07283 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.01245 + CZtot = -0.84305 Cntot = -0.00000 Cn'tot = 0.00000 + + CLtot = 0.84564 + CDtot = 0.03046 + CDvis = 0.00000 CDind = 0.03046 + CLff = 0.84693 CDff = 0.02849 | Trefftz + CYff = -0.00000 e = 0.8494 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.605420 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.835710 - x' mom. Cl'| Cla = -0.000004 Clb = -0.247102 - y mom. Cm | Cma = -7.968892 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.301475 + z' force CL | CLa = 5.603395 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.835689 + x' mom. Cl'| Cla = -0.000001 Clb = -0.247259 + y mom. Cm | Cma = -7.966436 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.301519 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.369083 CLr = -0.000003 - y force CY | CYp = 0.133998 CYq = -0.000005 CYr = 1.028414 - x' mom. Cl'| Clp = -0.452821 Clq = -0.000022 Clr = 0.291314 - y mom. Cm | Cmp = -0.000015 Cmq = -78.846008 Cmr = 0.000007 - z' mom. Cn'| Cnp = -0.070513 Cnq = 0.000004 Cnr = -0.554047 + z' force CL | CLp = 0.000001 CLq = 27.363400 CLr = -0.000001 + y force CY | CYp = 0.134339 CYq = -0.000001 CYr = 1.028479 + x' mom. Cl'| Clp = -0.452790 Clq = -0.000003 Clr = 0.291361 + y mom. Cm | Cmp = -0.000002 Cmq = -78.831230 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.070598 Cnq = 0.000000 Cnr = -0.554082 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000764 CLd2 = 0.024716 CLd3 = -0.000000 CLd4 = 0.011825 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000249 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000765 CLd2 = 0.024711 CLd3 = -0.000000 CLd4 = 0.011825 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000252 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001886 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000181 Cmd2 = -0.022838 Cmd3 = 0.000000 Cmd4 = -0.057793 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000082 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000027 CDffd2 = 0.001083 CDffd3 = -0.000000 CDffd4 = 0.001030 - span eff. | ed1 = -0.000367 ed2 = 0.017620 ed3 = 0.000000 ed4 = -0.006947 - - + y mom. Cm | Cmd1 = 0.000182 Cmd2 = -0.022836 Cmd3 = 0.000000 Cmd4 = -0.057793 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000078 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000027 CDffd2 = 0.001083 CDffd3 = -0.000000 CDffd4 = 0.001031 + span eff. | ed1 = -0.000368 ed2 = 0.017670 ed3 = 0.000000 ed4 = -0.006903 + + - Neutral point Xnp = 21.330524 + Neutral point Xnp = 21.330845 - Clb Cnr / Clr Cnb = 1.558873 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.559487 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_06.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_06.txt index c5838d3425..d99ebf5a1d 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_06.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_02_06.txt @@ -13,57 +13,57 @@ Run case: case_02_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.150 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.14289 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.42600 - CZtot = -1.12809 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.13577 - CDtot = 0.05517 - CDvis = 0.00000 CDind = 0.0551705 - CLff = 1.14056 CDff = 0.0514484 | Trefftz - CYff = -0.00000 e = 0.8532 | Plane - + Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.14397 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.42501 + CZtot = -1.12848 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 1.13633 + CDtot = 0.05417 + CDvis = 0.00000 CDind = 0.05417 + CLff = 1.14145 CDff = 0.05156 | Trefftz + CYff = -0.00000 e = 0.8527 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.496346 CLb = 0.000002 - y force CY | CYa = 0.000002 CYb = -0.837717 - x' mom. Cl'| Cla = -0.000004 Clb = -0.265722 - y mom. Cm | Cma = -7.781526 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.315123 + z' force CL | CLa = 5.494369 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.837662 + x' mom. Cl'| Cla = -0.000001 Clb = -0.265873 + y mom. Cm | Cma = -7.777928 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.315170 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.407410 CLr = -0.000004 - y force CY | CYp = 0.294742 CYq = -0.000003 CYr = 1.014688 - x' mom. Cl'| Clp = -0.441002 Clq = -0.000022 Clr = 0.328483 - y mom. Cm | Cmp = -0.000014 Cmq = -78.644539 Cmr = 0.000010 - z' mom. Cn'| Cnp = -0.143365 Cnq = 0.000004 Cnr = -0.561856 + z' force CL | CLp = 0.000001 CLq = 27.399256 CLr = -0.000001 + y force CY | CYp = 0.295121 CYq = -0.000001 CYr = 1.014722 + x' mom. Cl'| Clp = -0.440960 Clq = -0.000003 Clr = 0.328523 + y mom. Cm | Cmp = -0.000002 Cmq = -78.618454 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.143460 Cnq = 0.000000 Cnr = -0.561886 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000893 CLd2 = 0.024230 CLd3 = -0.000000 CLd4 = 0.011573 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000210 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000894 CLd2 = 0.024223 CLd3 = -0.000000 CLd4 = 0.011572 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000213 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001848 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000211 Cmd2 = -0.022380 Cmd3 = 0.000000 Cmd4 = -0.056877 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000131 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000037 CDffd2 = 0.001464 CDffd3 = -0.000000 CDffd4 = 0.001408 - span eff. | ed1 = -0.000267 ed2 = 0.012561 ed3 = 0.000000 ed4 = -0.005764 - - + y mom. Cm | Cmd1 = 0.000212 Cmd2 = -0.022378 Cmd3 = 0.000000 Cmd4 = -0.056873 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000127 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000037 CDffd2 = 0.001463 CDffd3 = -0.000000 CDffd4 = 0.001410 + span eff. | ed1 = -0.000267 ed2 = 0.012588 ed3 = 0.000000 ed4 = -0.005742 + + - Neutral point Xnp = 21.305637 + Neutral point Xnp = 21.305021 - Clb Cnr / Clr Cnb = 1.442311 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.442814 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_01.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_01.txt index a88370c85a..096983ad1d 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_01.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_01.txt @@ -13,57 +13,57 @@ Run case: case_03_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00049 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.25494 - CZtot = 0.04872 Cntot = -0.00000 Cn'tot = -0.00000 + CXtot = 0.00046 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.25568 + CZtot = 0.04783 Cntot = -0.00000 Cn'tot = -0.00000 - CLtot = -0.04871 + CLtot = -0.04781 CDtot = 0.00121 - CDvis = 0.00000 CDind = 0.0012134 - CLff = -0.04864 CDff = 0.0008616 | Trefftz - CYff = 0.00000 e = 0.0927 | Plane - + CDvis = 0.00000 CDind = 0.00121 + CLff = -0.04774 CDff = 0.00088 | Trefftz + CYff = 0.00000 e = 0.0877 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.784509 CLb = 0.000001 - y force CY | CYa = -0.000001 CYb = -0.820482 - x' mom. Cl'| Cla = -0.000004 Clb = -0.185838 - y mom. Cm | Cma = -8.107448 Cmb = -0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.275595 + z' force CL | CLa = 5.784994 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.820562 + x' mom. Cl'| Cla = -0.000000 Clb = -0.186015 + y mom. Cm | Cma = -8.108529 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.275621 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.613228 CLr = -0.000000 - y force CY | CYp = -0.346649 CYq = -0.000007 CYr = 0.974478 - x' mom. Cl'| Clp = -0.503399 Clq = -0.000024 Clr = 0.167875 - y mom. Cm | Cmp = -0.000016 Cmq = -79.051575 Cmr = 0.000000 - z' mom. Cn'| Cnp = 0.140201 Cnq = 0.000003 Cnr = -0.507824 + z' force CL | CLp = 0.000001 CLq = 27.618090 CLr = -0.000000 + y force CY | CYp = -0.346429 CYq = -0.000001 CYr = 0.974606 + x' mom. Cl'| Clp = -0.503415 Clq = -0.000003 Clr = 0.167936 + y mom. Cm | Cmp = -0.000002 Cmq = -79.068573 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.140131 Cnq = 0.000000 Cnr = -0.507867 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000595 CLd2 = 0.025715 CLd3 = -0.000000 CLd4 = 0.012249 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000364 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000595 CLd2 = 0.025716 CLd3 = -0.000000 CLd4 = 0.012251 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000366 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001961 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000083 Cmd2 = -0.023860 Cmd3 = 0.000000 Cmd4 = -0.059416 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000072 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000125 CDffd3 = 0.000000 CDffd4 = -0.000170 - span eff. | ed1 = 0.002031 ed2 = -0.084538 ed3 = 0.000000 ed4 = -0.028282 - - + y mom. Cm | Cmd1 = 0.000085 Cmd2 = -0.023858 Cmd3 = 0.000000 Cmd4 = -0.059425 + z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000076 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000125 CDffd3 = 0.000000 CDffd4 = -0.000169 + span eff. | ed1 = 0.001968 ed2 = -0.081944 ed3 = 0.000000 ed4 = -0.028016 + + - Neutral point Xnp = 21.245567 + Neutral point Xnp = 21.245861 - Clb Cnr / Clr Cnb = 2.039817 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 2.040996 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_02.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_02.txt index be93b9d00b..80dcea2d11 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_02.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_02.txt @@ -13,57 +13,57 @@ Run case: case_03_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = -0.00216 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.02926 - CZtot = -0.15336 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.15336 - CDtot = 0.00216 - CDvis = 0.00000 CDind = 0.0021615 - CLff = 0.15331 CDff = 0.0014964 | Trefftz - CYff = 0.00000 e = 0.5300 | Plane - + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = -0.00209 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.02855 + CZtot = -0.15427 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.15427 + CDtot = 0.00209 + CDvis = 0.00000 CDind = 0.00209 + CLff = 0.15422 CDff = 0.00153 | Trefftz + CYff = 0.00000 e = 0.5252 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.790546 CLb = 0.000001 - y force CY | CYa = -0.000000 CYb = -0.826784 - x' mom. Cl'| Cla = -0.000004 Clb = -0.200806 - y mom. Cm | Cma = -8.169252 Cmb = -0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.280239 + z' force CL | CLa = 5.790949 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.826838 + x' mom. Cl'| Cla = -0.000001 Clb = -0.200983 + y mom. Cm | Cma = -8.169821 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.280268 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.626787 CLr = -0.000001 - y force CY | CYp = -0.241449 CYq = -0.000007 CYr = 1.001077 - x' mom. Cl'| Clp = -0.492311 Clq = -0.000024 Clr = 0.198141 - y mom. Cm | Cmp = -0.000017 Cmq = -79.376007 Cmr = 0.000002 - z' mom. Cn'| Cnp = 0.094713 Cnq = 0.000003 Cnr = -0.522171 + z' force CL | CLp = 0.000001 CLq = 27.630119 CLr = -0.000000 + y force CY | CYp = -0.241184 CYq = -0.000001 CYr = 1.001193 + x' mom. Cl'| Clp = -0.492326 Clq = -0.000003 Clr = 0.198202 + y mom. Cm | Cmp = -0.000002 Cmq = -79.386948 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.094634 Cnq = 0.000000 Cnr = -0.522212 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000606 CLd2 = 0.025694 CLd3 = -0.000000 CLd4 = 0.012252 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000340 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000607 CLd2 = 0.025693 CLd3 = -0.000000 CLd4 = 0.012253 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000342 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001958 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000105 Cmd2 = -0.023818 Cmd3 = 0.000000 Cmd4 = -0.059477 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000005 CDffd2 = 0.000156 CDffd3 = -0.000000 CDffd4 = 0.000106 - span eff. | ed1 = -0.002515 ed2 = 0.122039 ed3 = -0.000000 ed4 = 0.046904 - - + y mom. Cm | Cmd1 = 0.000106 Cmd2 = -0.023816 Cmd3 = 0.000000 Cmd4 = -0.059484 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000041 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000005 CDffd2 = 0.000156 CDffd3 = -0.000000 CDffd4 = 0.000107 + span eff. | ed1 = -0.002498 ed2 = 0.121262 ed3 = -0.000000 ed4 = 0.046378 + + Neutral point Xnp = 21.284580 - Clb Cnr / Clr Cnb = 1.888362 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.889397 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_03.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_03.txt index d4ed5b6d9b..4f3add30a2 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_03.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_03.txt @@ -13,57 +13,57 @@ Run case: case_03_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00592 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.31492 - CZtot = -0.35536 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.35535 - CDtot = 0.00649 - CDvis = 0.00000 CDind = 0.0064885 - CLff = 0.35508 CDff = 0.0053666 | Trefftz - CYff = -0.00000 e = 0.7928 | Plane - + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00615 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.31422 + CZtot = -0.35628 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.35627 + CDtot = 0.00629 + CDvis = 0.00000 CDind = 0.00629 + CLff = 0.35599 CDff = 0.00541 | Trefftz + CYff = -0.00000 e = 0.7897 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.779383 CLb = 0.000001 - y force CY | CYa = -0.000000 CYb = -0.832078 - x' mom. Cl'| Cla = -0.000004 Clb = -0.215414 - y mom. Cm | Cma = -8.191259 Cmb = -0.000002 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.285916 + z' force CL | CLa = 5.779913 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.832107 + x' mom. Cl'| Cla = -0.000001 Clb = -0.215590 + y mom. Cm | Cma = -8.191312 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.285949 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.642864 CLr = -0.000002 - y force CY | CYp = -0.134649 CYq = -0.000007 CYr = 1.020273 - x' mom. Cl'| Clp = -0.481697 Clq = -0.000024 Clr = 0.227179 - y mom. Cm | Cmp = -0.000016 Cmq = -79.603752 Cmr = 0.000004 - z' mom. Cn'| Cnp = 0.048123 Cnq = 0.000003 Cnr = -0.534809 + z' force CL | CLp = 0.000001 CLq = 27.644960 CLr = -0.000000 + y force CY | CYp = -0.134342 CYq = -0.000001 CYr = 1.020374 + x' mom. Cl'| Clp = -0.481710 Clq = -0.000003 Clr = 0.227239 + y mom. Cm | Cmp = -0.000002 Cmq = -79.608612 Cmr = 0.000001 + z' mom. Cn'| Cnp = 0.048035 Cnq = 0.000000 Cnr = -0.534848 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000634 CLd2 = 0.025606 CLd3 = -0.000000 CLd4 = 0.012217 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000315 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000634 CLd2 = 0.025605 CLd3 = -0.000000 CLd4 = 0.012218 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000318 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001950 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000127 Cmd2 = -0.023719 Cmd3 = 0.000000 Cmd4 = -0.059392 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000436 CDffd3 = -0.000000 CDffd4 = 0.000380 - span eff. | ed1 = -0.000994 ed2 = 0.049882 ed3 = 0.000000 ed4 = -0.001811 - - + y mom. Cm | Cmd1 = 0.000128 Cmd2 = -0.023716 Cmd3 = 0.000000 Cmd4 = -0.059398 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000006 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000435 CDffd3 = -0.000000 CDffd4 = 0.000381 + span eff. | ed1 = -0.000997 ed2 = 0.050070 ed3 = 0.000000 ed4 = -0.001603 + + - Neutral point Xnp = 21.312246 + Neutral point Xnp = 21.311735 - Clb Cnr / Clr Cnb = 1.773637 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.774543 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_04.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_04.txt index 40d435ed83..3cfc5ca93a 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_04.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_04.txt @@ -13,57 +13,57 @@ Run case: case_03_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.03805 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.74311 - CZtot = -0.65602 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.65684 - CDtot = 0.01927 - CDvis = 0.00000 CDind = 0.0192735 - CLff = 0.65685 CDff = 0.0171926 | Trefftz - CYff = -0.00000 e = 0.8468 | Plane - + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.03866 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.74239 + CZtot = -0.65694 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.65781 + CDtot = 0.01875 + CDvis = 0.00000 CDind = 0.01875 + CLff = 0.65776 CDff = 0.01727 | Trefftz + CYff = -0.00000 e = 0.8455 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.730510 CLb = 0.000002 - y force CY | CYa = 0.000000 CYb = -0.838118 - x' mom. Cl'| Cla = -0.000004 Clb = -0.236494 - y mom. Cm | Cma = -8.149464 Cmb = -0.000002 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.296307 + z' force CL | CLa = 5.731604 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.838108 + x' mom. Cl'| Cla = -0.000001 Clb = -0.236669 + y mom. Cm | Cma = -8.148743 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.296345 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.671524 CLr = -0.000003 - y force CY | CYp = 0.027409 CYq = -0.000005 CYr = 1.034991 - x' mom. Cl'| Clp = -0.466900 Clq = -0.000023 Clr = 0.268614 - y mom. Cm | Cmp = -0.000016 Cmq = -79.763451 Cmr = 0.000006 - z' mom. Cn'| Cnp = -0.023447 Cnq = 0.000004 Cnr = -0.550319 + z' force CL | CLp = 0.000001 CLq = 27.672323 CLr = -0.000000 + y force CY | CYp = 0.027779 CYq = -0.000001 CYr = 1.035064 + x' mom. Cl'| Clp = -0.466913 Clq = -0.000003 Clr = 0.268673 + y mom. Cm | Cmp = -0.000002 Cmq = -79.759201 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.023548 Cnq = 0.000001 Cnr = -0.550353 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000707 CLd2 = 0.025350 CLd3 = -0.000000 CLd4 = 0.012095 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000277 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000707 CLd2 = 0.025348 CLd3 = -0.000000 CLd4 = 0.012096 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000280 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001928 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000159 Cmd2 = -0.023462 Cmd3 = 0.000000 Cmd4 = -0.058994 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000022 CDffd2 = 0.000849 CDffd3 = -0.000000 CDffd4 = 0.000786 - span eff. | ed1 = -0.000483 ed2 = 0.023735 ed3 = 0.000000 ed4 = -0.007540 - - + y mom. Cm | Cmd1 = 0.000160 Cmd2 = -0.023458 Cmd3 = 0.000000 Cmd4 = -0.058997 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000045 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000022 CDffd2 = 0.000849 CDffd3 = -0.000000 CDffd4 = 0.000788 + span eff. | ed1 = -0.000484 ed2 = 0.023819 ed3 = 0.000000 ed4 = -0.007462 + + - Neutral point Xnp = 21.332550 + Neutral point Xnp = 21.330868 - Clb Cnr / Clr Cnb = 1.635175 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.635917 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_05.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_05.txt index f2a6575fff..28b8ccbbd5 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_05.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_05.txt @@ -13,57 +13,57 @@ Run case: case_03_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.07266 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.02634 - CZtot = -0.85349 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.85599 - CDtot = 0.03190 - CDvis = 0.00000 CDind = 0.0318987 - CLff = 0.85708 CDff = 0.0290343 | Trefftz - CYff = -0.00000 e = 0.8537 | Plane - + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.07360 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.02559 + CZtot = -0.85440 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.85700 + CDtot = 0.03107 + CDvis = 0.00000 CDind = 0.03107 + CLff = 0.85799 CDff = 0.02912 | Trefftz + CYff = -0.00000 e = 0.8529 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.676805 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.840869 - x' mom. Cl'| Cla = -0.000004 Clb = -0.249894 - y mom. Cm | Cma = -8.071924 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.304434 + z' force CL | CLa = 5.678520 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.840833 + x' mom. Cl'| Cla = -0.000001 Clb = -0.250067 + y mom. Cm | Cma = -8.070692 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.304475 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 27.693516 CLr = -0.000004 - y force CY | CYp = 0.135920 CYq = -0.000005 CYr = 1.035349 - x' mom. Cl'| Clp = -0.457921 Clq = -0.000024 Clr = 0.294963 - y mom. Cm | Cmp = -0.000015 Cmq = -79.748459 Cmr = 0.000008 - z' mom. Cn'| Cnp = -0.072010 Cnq = 0.000004 Cnr = -0.558224 + z' force CL | CLp = 0.000001 CLq = 27.693834 CLr = -0.000000 + y force CY | CYp = 0.136329 CYq = -0.000001 CYr = 1.035401 + x' mom. Cl'| Clp = -0.457935 Clq = -0.000003 Clr = 0.295020 + y mom. Cm | Cmp = -0.000002 Cmq = -79.738136 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.072119 Cnq = 0.000000 Cnr = -0.558254 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000775 CLd2 = 0.025098 CLd3 = -0.000000 CLd4 = 0.011969 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000251 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000775 CLd2 = 0.025096 CLd3 = -0.000000 CLd4 = 0.011969 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000254 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001909 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000180 Cmd2 = -0.023220 Cmd3 = 0.000000 Cmd4 = -0.058550 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000082 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000028 CDffd2 = 0.001119 CDffd3 = -0.000000 CDffd4 = 0.001052 - span eff. | ed1 = -0.000361 ed2 = 0.017463 ed3 = 0.000000 ed4 = -0.006958 - - + y mom. Cm | Cmd1 = 0.000181 Cmd2 = -0.023216 Cmd3 = 0.000000 Cmd4 = -0.058551 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000079 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000028 CDffd2 = 0.001119 CDffd3 = -0.000000 CDffd4 = 0.001053 + span eff. | ed1 = -0.000361 ed2 = 0.017513 ed3 = 0.000000 ed4 = -0.006914 + + - Neutral point Xnp = 21.331680 + Neutral point Xnp = 21.328943 - Clb Cnr / Clr Cnb = 1.553474 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.554119 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_06.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_06.txt index a3d60889b5..7e7fff48b5 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_06.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_03_06.txt @@ -13,57 +13,57 @@ Run case: case_03_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.250 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.14394 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.44440 - CZtot = -1.14283 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = 1.15047 - CDtot = 0.05670 - CDvis = 0.00000 CDind = 0.0567018 - CLff = 1.15539 CDff = 0.0525895 | Trefftz - CYff = -0.00000 e = 0.8565 | Plane - + Mach = 0.250 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.14551 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.44356 + CZtot = -1.14371 Cntot = -0.00000 Cn'tot = 0.00000 + + CLtot = 1.15160 + CDtot = 0.05531 + CDvis = 0.00000 CDind = 0.05531 + CLff = 1.15629 CDff = 0.05270 | Trefftz + CYff = -0.00000 e = 0.8560 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.565473 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.843073 - x' mom. Cl'| Cla = -0.000004 Clb = -0.268850 - y mom. Cm | Cma = -7.882054 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.318327 + z' force CL | CLa = 5.568469 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.843000 + x' mom. Cl'| Cla = -0.000001 Clb = -0.269021 + y mom. Cm | Cma = -7.880065 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.318373 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 27.730574 CLr = -0.000005 - y force CY | CYp = 0.298072 CYq = -0.000004 CYr = 1.021703 - x' mom. Cl'| Clp = -0.445968 Clq = -0.000023 Clr = 0.332839 - y mom. Cm | Cmp = -0.000015 Cmq = -79.543846 Cmr = 0.000010 - z' mom. Cn'| Cnp = -0.145633 Cnq = 0.000004 Cnr = -0.566246 + z' force CL | CLp = 0.000001 CLq = 27.730757 CLr = -0.000001 + y force CY | CYp = 0.298537 CYq = -0.000001 CYr = 1.021716 + x' mom. Cl'| Clp = -0.445983 Clq = -0.000003 Clr = 0.332896 + y mom. Cm | Cmp = -0.000002 Cmq = -79.524414 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.145755 Cnq = 0.000000 Cnr = -0.566269 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000905 CLd2 = 0.024603 CLd3 = -0.000000 CLd4 = 0.011713 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000212 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000905 CLd2 = 0.024602 CLd3 = -0.000000 CLd4 = 0.011713 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000215 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001870 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000210 Cmd2 = -0.022754 Cmd3 = 0.000000 Cmd4 = -0.057621 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000132 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000038 CDffd2 = 0.001512 CDffd3 = -0.000000 CDffd4 = 0.001438 - span eff. | ed1 = -0.000262 ed2 = 0.012454 ed3 = 0.000000 ed4 = -0.005778 - - + y mom. Cm | Cmd1 = 0.000211 Cmd2 = -0.022751 Cmd3 = 0.000000 Cmd4 = -0.057618 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000128 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000038 CDffd2 = 0.001511 CDffd3 = -0.000000 CDffd4 = 0.001439 + span eff. | ed1 = -0.000262 ed2 = 0.012481 ed3 = 0.000000 ed4 = -0.005756 + + - Neutral point Xnp = 21.307663 + Neutral point Xnp = 21.302921 - Clb Cnr / Clr Cnb = 1.436837 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.437354 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_01.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_01.txt index 5e9272a63b..6187f983a3 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_01.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_01.txt @@ -13,57 +13,57 @@ Run case: case_04_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00048 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.26769 - CZtot = 0.05045 Cntot = -0.00000 Cn'tot = -0.00000 + CXtot = 0.00044 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.26853 + CZtot = 0.04952 Cntot = -0.00000 Cn'tot = -0.00000 - CLtot = -0.05044 + CLtot = -0.04950 CDtot = 0.00128 - CDvis = 0.00000 CDind = 0.0012833 - CLff = -0.05038 CDff = 0.0009144 | Trefftz - CYff = 0.00000 e = 0.0936 | Plane - + CDvis = 0.00000 CDind = 0.00128 + CLff = -0.04942 CDff = 0.00093 | Trefftz + CYff = 0.00000 e = 0.0886 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.070913 CLb = 0.000001 - y force CY | CYa = -0.000001 CYb = -0.837418 - x' mom. Cl'| Cla = -0.000005 Clb = -0.192145 - y mom. Cm | Cma = -8.509398 Cmb = -0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.284857 + z' force CL | CLa = 6.070711 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.837487 + x' mom. Cl'| Cla = -0.000001 Clb = -0.192326 + y mom. Cm | Cma = -8.510468 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.284878 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 28.869560 CLr = -0.000000 - y force CY | CYp = -0.354712 CYq = -0.000008 CYr = 0.996514 - x' mom. Cl'| Clp = -0.524381 Clq = -0.000027 Clr = 0.172887 - y mom. Cm | Cmp = -0.000018 Cmq = -82.517746 Cmr = -0.000000 - z' mom. Cn'| Cnp = 0.142678 Cnq = 0.000003 Cnr = -0.520820 + z' force CL | CLp = 0.000001 CLq = 28.873974 CLr = -0.000000 + y force CY | CYp = -0.354446 CYq = -0.000001 CYr = 0.996635 + x' mom. Cl'| Clp = -0.524384 Clq = -0.000003 Clr = 0.172946 + y mom. Cm | Cmp = -0.000002 Cmq = -82.537949 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.142592 Cnq = 0.000000 Cnr = -0.520859 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000621 CLd2 = 0.027261 CLd3 = -0.000000 CLd4 = 0.012824 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000376 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000621 CLd2 = 0.027260 CLd3 = -0.000000 CLd4 = 0.012826 + y force CY | CYd1 = 0.000000 CYd2 = 0.000000 CYd3 = 0.000379 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002050 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000069 Cmd2 = -0.025404 Cmd3 = 0.000000 Cmd4 = -0.062427 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000074 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000131 CDffd3 = 0.000000 CDffd4 = -0.000189 - span eff. | ed1 = 0.002080 ed2 = -0.087888 ed3 = 0.000000 ed4 = -0.028193 - - + y mom. Cm | Cmd1 = 0.000070 Cmd2 = -0.025401 Cmd3 = 0.000000 Cmd4 = -0.062438 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000077 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000132 CDffd3 = 0.000000 CDffd4 = -0.000188 + span eff. | ed1 = 0.002015 ed2 = -0.085141 ed3 = 0.000000 ed4 = -0.027963 + + - Neutral point Xnp = 21.245937 + Neutral point Xnp = 21.246881 - Clb Cnr / Clr Cnb = 2.032016 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 2.033240 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_02.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_02.txt index b2517f0215..8ac96d1321 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_02.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_02.txt @@ -13,57 +13,57 @@ Run case: case_04_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = -0.00233 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.03060 - CZtot = -0.16165 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.16165 - CDtot = 0.00233 - CDvis = 0.00000 CDind = 0.0023262 - CLff = 0.16158 CDff = 0.0016067 | Trefftz - CYff = 0.00000 e = 0.5483 | Plane - + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = -0.00224 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.02978 + CZtot = -0.16256 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.16256 + CDtot = 0.00224 + CDvis = 0.00000 CDind = 0.00224 + CLff = 0.16254 CDff = 0.00164 | Trefftz + CYff = 0.00000 e = 0.5433 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.077710 CLb = 0.000002 - y force CY | CYa = -0.000000 CYb = -0.844359 - x' mom. Cl'| Cla = -0.000005 Clb = -0.208162 - y mom. Cm | Cma = -8.574489 Cmb = -0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.289821 + z' force CL | CLa = 6.076555 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.844396 + x' mom. Cl'| Cla = -0.000001 Clb = -0.208341 + y mom. Cm | Cma = -8.574608 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.289846 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000010 CLq = 28.887135 CLr = -0.000001 - y force CY | CYp = -0.246157 CYq = -0.000007 CYr = 1.024500 - x' mom. Cl'| Clp = -0.513042 Clq = -0.000027 Clr = 0.205288 - y mom. Cm | Cmp = -0.000018 Cmq = -82.858521 Cmr = 0.000002 - z' mom. Cn'| Cnp = 0.095401 Cnq = 0.000003 Cnr = -0.535841 + z' force CL | CLp = 0.000001 CLq = 28.888634 CLr = -0.000000 + y force CY | CYp = -0.245831 CYq = -0.000001 CYr = 1.024608 + x' mom. Cl'| Clp = -0.513036 Clq = -0.000003 Clr = 0.205345 + y mom. Cm | Cmp = -0.000002 Cmq = -82.870773 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.095305 Cnq = 0.000000 Cnr = -0.535878 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000633 CLd2 = 0.027239 CLd3 = -0.000000 CLd4 = 0.012827 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000352 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000632 CLd2 = 0.027237 CLd3 = -0.000000 CLd4 = 0.012829 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000354 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002046 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000092 Cmd2 = -0.025363 Cmd3 = 0.000000 Cmd4 = -0.062489 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000038 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000005 CDffd2 = 0.000185 CDffd3 = -0.000000 CDffd4 = 0.000110 - span eff. | ed1 = -0.002441 ed2 = 0.121684 ed3 = 0.000000 ed4 = 0.049157 - - + y mom. Cm | Cmd1 = 0.000093 Cmd2 = -0.025359 Cmd3 = 0.000000 Cmd4 = -0.062497 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000042 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000005 CDffd2 = 0.000184 CDffd3 = -0.000000 CDffd4 = 0.000111 + span eff. | ed1 = -0.002428 ed2 = 0.121003 ed3 = 0.000000 ed4 = 0.048590 + + - Neutral point Xnp = 21.284655 + Neutral point Xnp = 21.285873 - Clb Cnr / Clr Cnb = 1.874756 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.875812 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_03.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_03.txt index d24335e0d9..59d7c6b5c5 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_03.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_03.txt @@ -13,57 +13,57 @@ Run case: case_04_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00598 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.33044 - CZtot = -0.37367 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.37365 - CDtot = 0.00707 - CDvis = 0.00000 CDind = 0.0070657 - CLff = 0.37334 CDff = 0.0058163 | Trefftz - CYff = -0.00000 e = 0.8086 | Plane - + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00626 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.32961 + CZtot = -0.37452 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.37451 + CDtot = 0.00681 + CDvis = 0.00000 CDind = 0.00681 + CLff = 0.37430 CDff = 0.00587 | Trefftz + CYff = 0.00000 e = 0.8056 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.066004 CLb = 0.000002 - y force CY | CYa = -0.000000 CYb = -0.850271 - x' mom. Cl'| Cla = -0.000005 Clb = -0.223794 - y mom. Cm | Cma = -8.597807 Cmb = -0.000002 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.295891 + z' force CL | CLa = 6.064164 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.850276 + x' mom. Cl'| Cla = -0.000001 Clb = -0.223970 + y mom. Cm | Cma = -8.596974 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.295919 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 28.906120 CLr = -0.000002 - y force CY | CYp = -0.135914 CYq = -0.000006 CYr = 1.044845 - x' mom. Cl'| Clp = -0.502148 Clq = -0.000027 Clr = 0.236405 - y mom. Cm | Cmp = -0.000017 Cmq = -83.098343 Cmr = 0.000004 - z' mom. Cn'| Cnp = 0.046974 Cnq = 0.000003 Cnr = -0.549140 + z' force CL | CLp = 0.000001 CLq = 28.905031 CLr = -0.000000 + y force CY | CYp = -0.135529 CYq = -0.000001 CYr = 1.044935 + x' mom. Cl'| Clp = -0.502134 Clq = -0.000003 Clr = 0.236460 + y mom. Cm | Cmp = -0.000002 Cmq = -83.102646 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.046869 Cnq = 0.000000 Cnr = -0.549174 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000663 CLd2 = 0.027146 CLd3 = -0.000000 CLd4 = 0.012791 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000326 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000662 CLd2 = 0.027142 CLd3 = -0.000000 CLd4 = 0.012792 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000329 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002038 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000115 Cmd2 = -0.025259 Cmd3 = 0.000000 Cmd4 = -0.062398 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000013 CDffd2 = 0.000498 CDffd3 = -0.000000 CDffd4 = 0.000408 - span eff. | ed1 = -0.000929 ed2 = 0.048248 ed3 = 0.000000 ed4 = -0.001498 - - + y mom. Cm | Cmd1 = 0.000116 Cmd2 = -0.025256 Cmd3 = 0.000000 Cmd4 = -0.062404 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000006 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000013 CDffd2 = 0.000498 CDffd3 = -0.000000 CDffd4 = 0.000409 + span eff. | ed1 = -0.000933 ed2 = 0.048467 ed3 = 0.000000 ed4 = -0.001293 + + - Neutral point Xnp = 21.312466 + Neutral point Xnp = 21.313705 - Clb Cnr / Clr Cnb = 1.756891 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.757806 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_04.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_04.txt index 00b7adafe8..a18c1f95b6 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_04.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_04.txt @@ -13,57 +13,57 @@ Run case: case_04_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.03916 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.77989 - CZtot = -0.68929 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.69008 - CDtot = 0.02106 - CDvis = 0.00000 CDind = 0.0210622 - CLff = 0.69005 CDff = 0.0186758 | Trefftz - CYff = -0.00000 e = 0.8603 | Plane - + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.03990 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.77898 + CZtot = -0.68998 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.69083 + CDtot = 0.02038 + CDvis = 0.00000 CDind = 0.02038 + CLff = 0.69101 CDff = 0.01875 | Trefftz + CYff = -0.00000 e = 0.8591 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.013879 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.857194 - x' mom. Cl'| Cla = -0.000005 Clb = -0.246354 - y mom. Cm | Cma = -8.554264 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.307002 + z' force CL | CLa = 6.011524 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.857151 + x' mom. Cl'| Cla = -0.000001 Clb = -0.246525 + y mom. Cm | Cma = -8.552011 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.307034 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 28.937044 CLr = -0.000003 - y force CY | CYp = 0.031438 CYq = -0.000006 CYr = 1.060831 - x' mom. Cl'| Clp = -0.486889 Clq = -0.000027 Clr = 0.280850 - y mom. Cm | Cmp = -0.000017 Cmq = -83.268173 Cmr = 0.000007 - z' mom. Cn'| Cnp = -0.027434 Cnq = 0.000004 Cnr = -0.565604 + z' force CL | CLp = 0.000001 CLq = 28.932705 CLr = -0.000000 + y force CY | CYp = 0.031909 CYq = -0.000001 CYr = 1.060885 + x' mom. Cl'| Clp = -0.486865 Clq = -0.000004 Clr = 0.280900 + y mom. Cm | Cmp = -0.000002 Cmq = -83.260551 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.027553 Cnq = 0.000000 Cnr = -0.565633 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000740 CLd2 = 0.026874 CLd3 = -0.000000 CLd4 = 0.012662 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000287 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000737 CLd2 = 0.026869 CLd3 = -0.000000 CLd4 = 0.012663 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000290 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002016 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000149 Cmd2 = -0.024990 Cmd3 = 0.000000 Cmd4 = -0.061976 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000050 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000024 CDffd2 = 0.000963 CDffd3 = -0.000000 CDffd4 = 0.000849 - span eff. | ed1 = -0.000451 ed2 = 0.022886 ed3 = 0.000000 ed4 = -0.007515 - - + y mom. Cm | Cmd1 = 0.000150 Cmd2 = -0.024986 Cmd3 = 0.000000 Cmd4 = -0.061978 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000047 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000024 CDffd2 = 0.000962 CDffd3 = -0.000000 CDffd4 = 0.000850 + span eff. | ed1 = -0.000452 ed2 = 0.022975 ed3 = 0.000000 ed4 = -0.007437 + + - Neutral point Xnp = 21.333828 + Neutral point Xnp = 21.334602 - Clb Cnr / Clr Cnb = 1.616057 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.616803 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_05.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_05.txt index 0250be4114..5d411517a0 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_05.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_05.txt @@ -13,57 +13,57 @@ Run case: case_04_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.07495 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.07719 - CZtot = -0.89661 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.89906 - CDtot = 0.03488 - CDvis = 0.00000 CDind = 0.0348820 - CLff = 0.90020 CDff = 0.0315514 | Trefftz - CYff = -0.00000 e = 0.8666 | Plane - + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.07609 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.07618 + CZtot = -0.89713 Cntot = -0.00000 Cn'tot = 0.00000 + + CLtot = 0.89972 + CDtot = 0.03381 + CDvis = 0.00000 CDind = 0.03381 + CLff = 0.90115 CDff = 0.03165 | Trefftz + CYff = -0.00000 e = 0.8658 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.956406 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.860505 - x' mom. Cl'| Cla = -0.000005 Clb = -0.260695 - y mom. Cm | Cma = -8.473093 Cmb = -0.000003 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.315694 + z' force CL | CLa = 5.954054 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.860431 + x' mom. Cl'| Cla = -0.000001 Clb = -0.260862 + y mom. Cm | Cma = -8.469911 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.315729 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000009 CLq = 28.959135 CLr = -0.000004 - y force CY | CYp = 0.143539 CYq = -0.000005 CYr = 1.061724 - x' mom. Cl'| Clp = -0.477582 Clq = -0.000027 Clr = 0.309130 - y mom. Cm | Cmp = -0.000016 Cmq = -83.254616 Cmr = 0.000008 - z' mom. Cn'| Cnp = -0.077940 Cnq = 0.000004 Cnr = -0.574112 + z' force CL | CLp = 0.000001 CLq = 28.953077 CLr = -0.000000 + y force CY | CYp = 0.144065 CYq = -0.000001 CYr = 1.061750 + x' mom. Cl'| Clp = -0.477551 Clq = -0.000003 Clr = 0.309177 + y mom. Cm | Cmp = -0.000002 Cmq = -83.239044 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.078069 Cnq = 0.000001 Cnr = -0.574136 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000812 CLd2 = 0.026606 CLd3 = -0.000000 CLd4 = 0.012529 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000261 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000809 CLd2 = 0.026600 CLd3 = -0.000000 CLd4 = 0.012529 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000264 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001995 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000172 Cmd2 = -0.024735 Cmd3 = 0.000000 Cmd4 = -0.061507 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000085 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000031 CDffd2 = 0.001265 CDffd3 = -0.000000 CDffd4 = 0.001137 - span eff. | ed1 = -0.000337 ed2 = 0.016854 ed3 = 0.000000 ed4 = -0.006971 - - + y mom. Cm | Cmd1 = 0.000172 Cmd2 = -0.024731 Cmd3 = 0.000000 Cmd4 = -0.061507 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000081 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000031 CDffd2 = 0.001265 CDffd3 = -0.000000 CDffd4 = 0.001138 + span eff. | ed1 = -0.000338 ed2 = 0.016907 ed3 = 0.000000 ed4 = -0.006927 + + - Neutral point Xnp = 21.334242 + Neutral point Xnp = 21.334356 - Clb Cnr / Clr Cnb = 1.533632 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.534281 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_06.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_06.txt index 9bd7807be8..fc14e2e9c7 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_06.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_04_06.txt @@ -13,57 +13,57 @@ Run case: case_04_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.450 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.14867 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.51603 - CZtot = -1.20040 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = 1.20798 - CDtot = 0.06203 - CDvis = 0.00000 CDind = 0.0620319 - CLff = 1.21327 CDff = 0.0571619 | Trefftz - CYff = -0.00000 e = 0.8690 | Plane - + Mach = 0.450 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.15058 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.51482 + CZtot = -1.20062 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 1.20853 + CDtot = 0.06019 + CDvis = 0.00000 CDind = 0.06019 + CLff = 1.21422 CDff = 0.05728 | Trefftz + CYff = -0.00000 e = 0.8685 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 5.837096 CLb = 0.000002 - y force CY | CYa = 0.000002 CYb = -0.863506 - x' mom. Cl'| Cla = -0.000005 Clb = -0.280983 - y mom. Cm | Cma = -8.274118 Cmb = -0.000004 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.330554 + z' force CL | CLa = 5.835274 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.863384 + x' mom. Cl'| Cla = -0.000001 Clb = -0.281144 + y mom. Cm | Cma = -8.269568 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.330592 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000008 CLq = 28.994232 CLr = -0.000005 - y force CY | CYp = 0.311124 CYq = -0.000004 CYr = 1.048406 - x' mom. Cl'| Clp = -0.465118 Clq = -0.000026 Clr = 0.349789 - y mom. Cm | Cmp = -0.000015 Cmq = -83.044128 Cmr = 0.000011 - z' mom. Cn'| Cnp = -0.154546 Cnq = 0.000004 Cnr = -0.582976 + z' force CL | CLp = 0.000001 CLq = 28.986271 CLr = -0.000001 + y force CY | CYp = 0.311729 CYq = -0.000002 CYr = 1.048383 + x' mom. Cl'| Clp = -0.465079 Clq = -0.000004 Clr = 0.349829 + y mom. Cm | Cmp = -0.000002 Cmq = -83.016663 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.154691 Cnq = 0.000001 Cnr = -0.582991 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000950 CLd2 = 0.026079 CLd3 = -0.000000 CLd4 = 0.012259 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000220 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000946 CLd2 = 0.026073 CLd3 = -0.000000 CLd4 = 0.012258 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000223 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.001955 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000205 Cmd2 = -0.024244 Cmd3 = 0.000000 Cmd4 = -0.060527 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000135 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000042 CDffd2 = 0.001706 CDffd3 = -0.000000 CDffd4 = 0.001556 - span eff. | ed1 = -0.000246 ed2 = 0.012037 ed3 = 0.000000 ed4 = -0.005808 - - + y mom. Cm | Cmd1 = 0.000205 Cmd2 = -0.024239 Cmd3 = 0.000000 Cmd4 = -0.060523 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000132 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000042 CDffd2 = 0.001705 CDffd3 = -0.000000 CDffd4 = 0.001558 + span eff. | ed1 = -0.000246 ed2 = 0.012066 ed3 = 0.000000 ed4 = -0.005786 + + - Neutral point Xnp = 21.313017 + Neutral point Xnp = 21.311588 - Clb Cnr / Clr Cnb = 1.416713 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.417239 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_01.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_01.txt index f7cf0472a1..708b2d31f1 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_01.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_01.txt @@ -13,57 +13,57 @@ Run case: case_05_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 - CXtot = 0.00043 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = 0.00000 Cmtot = 0.29265 - CZtot = 0.05367 Cntot = -0.00000 Cn'tot = -0.00000 + CXtot = 0.00040 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00000 Cmtot = 0.29369 + CZtot = 0.05263 Cntot = -0.00000 Cn'tot = -0.00000 - CLtot = -0.05366 + CLtot = -0.05261 CDtot = 0.00144 - CDvis = 0.00000 CDind = 0.0014392 - CLff = -0.05361 CDff = 0.0010232 | Trefftz - CYff = 0.00000 e = 0.0948 | Plane - + CDvis = 0.00000 CDind = 0.00144 + CLff = -0.05256 CDff = 0.00104 | Trefftz + CYff = 0.00000 e = 0.0895 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.647680 CLb = 0.000001 - y force CY | CYa = -0.000001 CYb = -0.869035 - x' mom. Cl'| Cla = -0.000006 Clb = -0.204159 - y mom. Cm | Cma = -9.309816 Cmb = 0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.302203 + z' force CL | CLa = 6.648695 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.869112 + x' mom. Cl'| Cla = -0.000001 Clb = -0.204360 + y mom. Cm | Cma = -9.311188 Cmb = 0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.302218 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000011 CLq = 31.382446 CLr = 0.000000 - y force CY | CYp = -0.369587 CYq = -0.000006 CYr = 1.037846 - x' mom. Cl'| Clp = -0.565229 Clq = -0.000032 Clr = 0.182366 - y mom. Cm | Cmp = -0.000021 Cmq = -89.391586 Cmr = -0.000002 - z' mom. Cn'| Cnp = 0.146974 Cnq = 0.000002 Cnr = -0.545221 + z' force CL | CLp = 0.000002 CLq = 31.388918 CLr = 0.000000 + y force CY | CYp = -0.369368 CYq = -0.000001 CYr = 1.037957 + x' mom. Cl'| Clp = -0.565252 Clq = -0.000004 Clr = 0.182420 + y mom. Cm | Cmp = -0.000003 Cmq = -89.410027 Cmr = -0.000000 + z' mom. Cn'| Cnp = 0.146890 Cnq = 0.000000 Cnr = -0.545251 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000671 CLd2 = 0.030462 CLd3 = -0.000000 CLd4 = 0.013979 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000401 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000670 CLd2 = 0.030464 CLd3 = -0.000000 CLd4 = 0.013982 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000404 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002224 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000032 Cmd2 = -0.028650 Cmd3 = 0.000000 Cmd4 = -0.068529 - z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000077 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000144 CDffd3 = 0.000000 CDffd4 = -0.000231 - span eff. | ed1 = 0.002162 ed2 = -0.094369 ed3 = 0.000000 ed4 = -0.027909 - - + y mom. Cm | Cmd1 = 0.000033 Cmd2 = -0.028648 Cmd3 = 0.000000 Cmd4 = -0.068540 + z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000081 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000144 CDffd3 = 0.000000 CDffd4 = -0.000230 + span eff. | ed1 = 0.002092 ed2 = -0.091304 ed3 = 0.000000 ed4 = -0.027751 + + - Neutral point Xnp = 21.240829 + Neutral point Xnp = 21.240799 - Clb Cnr / Clr Cnb = 2.019753 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 2.021153 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_02.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_02.txt index 7a150d1e7e..467fd22084 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_02.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_02.txt @@ -13,57 +13,57 @@ Run case: case_05_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = -0.00266 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.03371 - CZtot = -0.17861 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.17861 - CDtot = 0.00266 - CDvis = 0.00000 CDind = 0.0026568 - CLff = 0.17849 CDff = 0.0018435 | Trefftz - CYff = 0.00000 e = 0.5831 | Plane - + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = -0.00263 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.03273 + CZtot = -0.17970 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.17970 + CDtot = 0.00263 + CDvis = 0.00000 CDind = 0.00263 + CLff = 0.17954 CDff = 0.00188 | Trefftz + CYff = -0.00000 e = 0.5777 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.656627 CLb = 0.000001 - y force CY | CYa = -0.000000 CYb = -0.877301 - x' mom. Cl'| Cla = -0.000006 Clb = -0.222345 - y mom. Cm | Cma = -9.381839 Cmb = 0.000000 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.307808 + z' force CL | CLa = 6.658348 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.877360 + x' mom. Cl'| Cla = -0.000001 Clb = -0.222548 + y mom. Cm | Cma = -9.383224 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.307830 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000011 CLq = 31.410391 CLr = -0.000001 - y force CY | CYp = -0.254499 CYq = -0.000007 CYr = 1.068634 - x' mom. Cl'| Clp = -0.553438 Clq = -0.000032 Clr = 0.219128 - y mom. Cm | Cmp = -0.000021 Cmq = -89.765358 Cmr = 0.000000 - z' mom. Cn'| Cnp = 0.096147 Cnq = 0.000003 Cnr = -0.561585 + z' force CL | CLp = 0.000002 CLq = 31.416607 CLr = -0.000000 + y force CY | CYp = -0.254269 CYq = -0.000001 CYr = 1.068736 + x' mom. Cl'| Clp = -0.553469 Clq = -0.000004 Clr = 0.219183 + y mom. Cm | Cmp = -0.000003 Cmq = -89.778938 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.096059 Cnq = 0.000000 Cnr = -0.561614 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000685 CLd2 = 0.030442 CLd3 = -0.000000 CLd4 = 0.013983 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000375 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000683 CLd2 = 0.030444 CLd3 = -0.000000 CLd4 = 0.013985 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000378 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002220 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000058 Cmd2 = -0.028610 Cmd3 = 0.000000 Cmd4 = -0.068591 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000040 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000007 CDffd2 = 0.000249 CDffd3 = -0.000000 CDffd4 = 0.000117 - span eff. | ed1 = -0.002265 ed2 = 0.119916 ed3 = 0.000000 ed4 = 0.053930 - - + y mom. Cm | Cmd1 = 0.000058 Cmd2 = -0.028609 Cmd3 = 0.000000 Cmd4 = -0.068599 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000044 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000007 CDffd2 = 0.000248 CDffd3 = -0.000000 CDffd4 = 0.000119 + span eff. | ed1 = -0.002257 ed2 = 0.119447 ed3 = 0.000000 ed4 = 0.053270 + + - Neutral point Xnp = 21.278681 + Neutral point Xnp = 21.278019 - Clb Cnr / Clr Cnb = 1.851246 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.852440 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_03.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_03.txt index d40b3820e2..041e88a584 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_03.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_03.txt @@ -13,57 +13,57 @@ Run case: case_05_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00611 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.36179 - CZtot = -0.41085 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.41082 - CDtot = 0.00823 - CDvis = 0.00000 CDind = 0.0082293 - CLff = 0.41037 CDff = 0.0067847 | Trefftz - CYff = -0.00000 e = 0.8375 | Plane - + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00625 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.36085 + CZtot = -0.41202 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.41198 + CDtot = 0.00813 + CDvis = 0.00000 CDind = 0.00813 + CLff = 0.41142 CDff = 0.00684 | Trefftz + CYff = -0.00000 e = 0.8345 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.644392 CLb = 0.000001 - y force CY | CYa = 0.000000 CYb = -0.884497 - x' mom. Cl'| Cla = -0.000006 Clb = -0.240095 - y mom. Cm | Cma = -9.408151 Cmb = -0.000000 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.314669 + z' force CL | CLa = 6.646931 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.884540 + x' mom. Cl'| Cla = -0.000001 Clb = -0.240300 + y mom. Cm | Cma = -9.409548 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.314697 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000011 CLq = 31.437168 CLr = -0.000002 - y force CY | CYp = -0.137543 CYq = -0.000006 CYr = 1.091318 - x' mom. Cl'| Clp = -0.542029 Clq = -0.000033 Clr = 0.254497 - y mom. Cm | Cmp = -0.000021 Cmq = -90.029785 Cmr = 0.000002 - z' mom. Cn'| Cnp = 0.044077 Cnq = 0.000004 Cnr = -0.576210 + z' force CL | CLp = 0.000002 CLq = 31.443344 CLr = -0.000000 + y force CY | CYp = -0.137305 CYq = -0.000001 CYr = 1.091412 + x' mom. Cl'| Clp = -0.542068 Clq = -0.000004 Clr = 0.254553 + y mom. Cm | Cmp = -0.000003 Cmq = -90.038460 Cmr = 0.000000 + z' mom. Cn'| Cnp = 0.043987 Cnq = 0.000000 Cnr = -0.576237 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000718 CLd2 = 0.030341 CLd3 = -0.000000 CLd4 = 0.013943 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000348 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000715 CLd2 = 0.030343 CLd3 = -0.000000 CLd4 = 0.013945 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000352 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002211 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000084 Cmd2 = -0.028501 Cmd3 = 0.000000 Cmd4 = -0.068485 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000003 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000016 CDffd2 = 0.000639 CDffd3 = -0.000000 CDffd4 = 0.000464 - span eff. | ed1 = -0.000799 ed2 = 0.044861 ed3 = 0.000000 ed4 = -0.000567 - - + y mom. Cm | Cmd1 = 0.000084 Cmd2 = -0.028500 Cmd3 = 0.000000 Cmd4 = -0.068492 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000007 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000016 CDffd2 = 0.000639 CDffd3 = -0.000000 CDffd4 = 0.000465 + span eff. | ed1 = -0.000804 ed2 = 0.045137 ed3 = 0.000000 ed4 = -0.000370 + + - Neutral point Xnp = 21.306442 + Neutral point Xnp = 21.305042 - Clb Cnr / Clr Cnb = 1.727533 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.728553 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_04.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_04.txt index 2efaef3577..b37e884d64 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_04.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_04.txt @@ -13,57 +13,57 @@ Run case: case_05_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.04140 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -0.85363 - CZtot = -0.75668 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.75740 - CDtot = 0.02471 - CDvis = 0.00000 CDind = 0.0247080 - CLff = 0.75716 CDff = 0.0218650 | Trefftz - CYff = -0.00000 e = 0.8847 | Plane - + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.04178 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.85277 + CZtot = -0.75798 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.75874 + CDtot = 0.02444 + CDvis = 0.00000 CDind = 0.02444 + CLff = 0.75822 CDff = 0.02196 | Trefftz + CYff = -0.00000 e = 0.8835 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.586445 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.893269 - x' mom. Cl'| Cla = -0.000006 Clb = -0.265716 - y mom. Cm | Cma = -9.361700 Cmb = -0.000001 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.327239 + z' force CL | CLa = 6.590400 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.893287 + x' mom. Cl'| Cla = -0.000001 Clb = -0.265923 + y mom. Cm | Cma = -9.363096 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.327277 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000010 CLq = 31.474854 CLr = -0.000003 - y force CY | CYp = 0.040143 CYq = -0.000006 CYr = 1.109920 - x' mom. Cl'| Clp = -0.525902 Clq = -0.000032 Clr = 0.305105 - y mom. Cm | Cmp = -0.000020 Cmq = -90.220665 Cmr = 0.000005 - z' mom. Cn'| Cnp = -0.035960 Cnq = 0.000005 Cnr = -0.594604 + z' force CL | CLp = 0.000001 CLq = 31.481407 CLr = -0.000000 + y force CY | CYp = 0.040394 CYq = -0.000001 CYr = 1.109999 + x' mom. Cl'| Clp = -0.525953 Clq = -0.000004 Clr = 0.305164 + y mom. Cm | Cmp = -0.000003 Cmq = -90.221992 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.036053 Cnq = 0.000000 Cnr = -0.594628 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000803 CLd2 = 0.030038 CLd3 = -0.000000 CLd4 = 0.013801 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000308 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000798 CLd2 = 0.030041 CLd3 = -0.000000 CLd4 = 0.013802 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000311 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002187 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000123 Cmd2 = -0.028208 Cmd3 = 0.000000 Cmd4 = -0.068013 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000052 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000029 CDffd2 = 0.001216 CDffd3 = -0.000000 CDffd4 = 0.000978 - span eff. | ed1 = -0.000387 ed2 = 0.021195 ed3 = 0.000000 ed4 = -0.007279 - - + y mom. Cm | Cmd1 = 0.000121 Cmd2 = -0.028208 Cmd3 = 0.000000 Cmd4 = -0.068017 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000048 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000029 CDffd2 = 0.001216 CDffd3 = -0.000000 CDffd4 = 0.000979 + span eff. | ed1 = -0.000388 ed2 = 0.021294 ed3 = 0.000000 ed4 = -0.007204 + + - Neutral point Xnp = 21.329332 + Neutral point Xnp = 21.326616 - Clb Cnr / Clr Cnb = 1.582454 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.583260 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_05.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_05.txt index 222dfffca6..7ce9fb845b 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_05.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_05.txt @@ -13,57 +13,57 @@ Run case: case_05_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.07951 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.17901 - CZtot = -0.98389 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.98625 - CDtot = 0.04099 - CDvis = 0.00000 CDind = 0.0409907 - CLff = 0.98726 CDff = 0.0369595 | Trefftz - CYff = -0.00000 e = 0.8899 | Plane - + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.08010 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.17820 + CZtot = -0.98532 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.98774 + CDtot = 0.04058 + CDvis = 0.00000 CDind = 0.04058 + CLff = 0.98832 CDff = 0.03707 | Trefftz + CYff = -0.00000 e = 0.8891 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.521772 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.897758 - x' mom. Cl'| Cla = -0.000006 Clb = -0.282005 - y mom. Cm | Cma = -9.273672 Cmb = -0.000001 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.337077 + z' force CL | CLa = 6.526785 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.897760 + x' mom. Cl'| Cla = -0.000001 Clb = -0.282213 + y mom. Cm | Cma = -9.275060 Cmb = -0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.337122 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000010 CLq = 31.498135 CLr = -0.000004 - y force CY | CYp = 0.159261 CYq = -0.000006 CYr = 1.111950 - x' mom. Cl'| Clp = -0.515967 Clq = -0.000032 Clr = 0.337343 - y mom. Cm | Cmp = -0.000019 Cmq = -90.210548 Cmr = 0.000007 - z' mom. Cn'| Cnp = -0.090321 Cnq = 0.000006 Cnr = -0.604345 + z' force CL | CLp = 0.000002 CLq = 31.505222 CLr = -0.000001 + y force CY | CYp = 0.159520 CYq = -0.000001 CYr = 1.112020 + x' mom. Cl'| Clp = -0.516026 Clq = -0.000004 Clr = 0.337404 + y mom. Cm | Cmp = -0.000003 Cmq = -90.206985 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.090416 Cnq = 0.000001 Cnr = -0.604367 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000883 CLd2 = 0.029738 CLd3 = -0.000000 CLd4 = 0.013653 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000280 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000877 CLd2 = 0.029742 CLd3 = -0.000000 CLd4 = 0.013654 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000283 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002165 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000148 Cmd2 = -0.027928 Cmd3 = 0.000000 Cmd4 = -0.067493 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000088 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000038 CDffd2 = 0.001593 CDffd3 = -0.000000 CDffd4 = 0.001313 - span eff. | ed1 = -0.000291 ed2 = 0.015651 ed3 = 0.000000 ed4 = -0.006854 - - + y mom. Cm | Cmd1 = 0.000146 Cmd2 = -0.027928 Cmd3 = 0.000000 Cmd4 = -0.067495 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000084 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000038 CDffd2 = 0.001592 CDffd3 = -0.000000 CDffd4 = 0.001314 + span eff. | ed1 = -0.000292 ed2 = 0.015708 ed3 = 0.000000 ed4 = -0.006812 + + - Neutral point Xnp = 21.331861 + Neutral point Xnp = 21.328136 - Clb Cnr / Clr Cnb = 1.498791 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.499474 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_06.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_06.txt index 51de893102..4375936da3 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_06.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_05_06.txt @@ -13,57 +13,57 @@ Run case: case_05_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.650 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.15809 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.65935 - CZtot = -1.31694 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = 1.32439 - CDtot = 0.07300 - CDvis = 0.00000 CDind = 0.0729982 - CLff = 1.33007 CDff = 0.0669791 | Trefftz - CYff = -0.00000 e = 0.8912 | Plane - + Mach = 0.650 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.15907 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.65861 + CZtot = -1.31860 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 1.32619 + CDtot = 0.07231 + CDvis = 0.00000 CDind = 0.07231 + CLff = 1.33112 CDff = 0.06712 | Trefftz + CYff = -0.00000 e = 0.8908 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 6.386848 CLb = 0.000002 - y force CY | CYa = 0.000002 CYb = -0.902439 - x' mom. Cl'| Cla = -0.000005 Clb = -0.305054 - y mom. Cm | Cma = -9.057111 Cmb = -0.000002 - z' mom. Cn'| Cna = 0.000001 Cnb = 0.353905 + z' force CL | CLa = 6.393570 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.902416 + x' mom. Cl'| Cla = -0.000001 Clb = -0.305262 + y mom. Cm | Cma = -9.058473 Cmb = -0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.353960 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000010 CLq = 31.530037 CLr = -0.000005 - y force CY | CYp = 0.337478 CYq = -0.000007 CYr = 1.099415 - x' mom. Cl'| Clp = -0.502514 Clq = -0.000031 Clr = 0.383702 - y mom. Cm | Cmp = -0.000019 Cmq = -89.989342 Cmr = 0.000010 - z' mom. Cn'| Cnp = -0.172850 Cnq = 0.000007 Cnr = -0.614947 + z' force CL | CLp = 0.000002 CLq = 31.538334 CLr = -0.000001 + y force CY | CYp = 0.337747 CYq = -0.000001 CYr = 1.099468 + x' mom. Cl'| Clp = -0.502584 Clq = -0.000004 Clr = 0.383769 + y mom. Cm | Cmp = -0.000003 Cmq = -89.978432 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.172945 Cnq = 0.000000 Cnr = -0.614967 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.001036 CLd2 = 0.029146 CLd3 = -0.000000 CLd4 = 0.013354 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000237 CYd4 = -0.000000 - x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002121 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000186 Cmd2 = -0.027383 Cmd3 = 0.000000 Cmd4 = -0.066409 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000141 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000052 CDffd2 = 0.002140 CDffd3 = -0.000000 CDffd4 = 0.001802 - span eff. | ed1 = -0.000213 ed2 = 0.011221 ed3 = 0.000000 ed4 = -0.005766 - - - - Neutral point Xnp = 21.315479 - - Clb Cnr / Clr Cnb = 1.381446 ( > 1 if spirally stable ) + z' force CL | CLd1 = -0.001029 CLd2 = 0.029150 CLd3 = -0.000000 CLd4 = 0.013354 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000240 CYd4 = -0.000000 + x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002122 Cld4 = -0.000000 + y mom. Cm | Cmd1 = 0.000183 Cmd2 = -0.027384 Cmd3 = 0.000000 Cmd4 = -0.066408 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000137 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000052 CDffd2 = 0.002139 CDffd3 = -0.000000 CDffd4 = 0.001803 + span eff. | ed1 = -0.000214 ed2 = 0.011251 ed3 = 0.000000 ed4 = -0.005744 + + + + Neutral point Xnp = 21.310068 + + Clb Cnr / Clr Cnb = 1.381976 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_01.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_01.txt index fc671b5736..bf668e8387 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_01.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_01.txt @@ -13,57 +13,57 @@ Run case: case_06_01 - Alpha = -2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = -2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00028 Cltot = 0.00000 Cl'tot = 0.00000 - CYtot = -0.00000 Cmtot = 0.34458 - CZtot = 0.05956 Cntot = -0.00000 Cn'tot = 0.00000 - - CLtot = -0.05953 - CDtot = 0.00179 - CDvis = 0.00000 CDind = 0.0017949 - CLff = -0.05953 CDff = 0.0012771 | Trefftz - CYff = -0.00000 e = 0.0937 | Plane - + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00021 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = -0.00000 Cmtot = 0.34617 + CZtot = 0.05825 Cntot = 0.00000 Cn'tot = 0.00000 + + CLtot = -0.05822 + CDtot = 0.00182 + CDvis = 0.00000 CDind = 0.00182 + CLff = -0.05823 CDff = 0.00130 | Trefftz + CYff = -0.00000 e = 0.0879 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 7.927435 CLb = 0.000001 - y force CY | CYa = -0.000000 CYb = -0.928996 - x' mom. Cl'| Cla = -0.000007 Clb = -0.227763 - y mom. Cm | Cma = -11.045035 Cmb = 0.000003 - z' mom. Cn'| Cna = -0.000001 Cnb = 0.335302 + z' force CL | CLa = 7.928590 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.929045 + x' mom. Cl'| Cla = -0.000001 Clb = -0.227994 + y mom. Cm | Cma = -11.046156 Cmb = 0.000001 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.335283 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000013 CLq = 36.914467 CLr = 0.000001 - y force CY | CYp = -0.397364 CYq = -0.000002 CYr = 1.117226 - x' mom. Cl'| Clp = -0.649073 Clq = -0.000040 Clr = 0.200853 - y mom. Cm | Cmp = -0.000025 Cmq =-104.222931 Cmr = -0.000005 - z' mom. Cn'| Cnp = 0.154004 Cnq = -0.000001 Cnr = -0.592228 + z' force CL | CLp = 0.000002 CLq = 36.920864 CLr = 0.000000 + y force CY | CYp = -0.397019 CYq = -0.000000 CYr = 1.117288 + x' mom. Cl'| Clp = -0.649087 Clq = -0.000005 Clr = 0.200882 + y mom. Cm | Cmp = -0.000003 Cmq =-104.242805 Cmr = -0.000001 + z' mom. Cn'| Cnp = 0.153834 Cnq = -0.000000 Cnr = -0.592224 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000763 CLd2 = 0.038074 CLd3 = -0.000000 CLd4 = 0.016573 - y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000453 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000764 CLd2 = 0.038075 CLd3 = -0.000000 CLd4 = 0.016576 + y force CY | CYd1 = 0.000000 CYd2 = -0.000000 CYd3 = 0.000457 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002586 Cld4 = -0.000000 - y mom. Cm | Cmd1 = -0.000091 Cmd2 = -0.036581 Cmd3 = 0.000000 Cmd4 = -0.082422 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000085 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000167 CDffd3 = 0.000000 CDffd4 = -0.000340 - span eff. | ed1 = 0.002248 ed2 = -0.107467 ed3 = 0.000000 ed4 = -0.027111 - - + y mom. Cm | Cmd1 = -0.000089 Cmd2 = -0.036577 Cmd3 = 0.000000 Cmd4 = -0.082438 + z' mom. Cn'| Cnd1 = -0.000000 Cnd2 = -0.000000 Cnd3 = -0.000090 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = 0.000002 CDffd2 = -0.000167 CDffd3 = 0.000000 CDffd4 = -0.000339 + span eff. | ed1 = 0.002166 ed2 = -0.103594 ed3 = 0.000000 ed4 = -0.027088 + + - Neutral point Xnp = 21.210365 + Neutral point Xnp = 21.210104 - Clb Cnr / Clr Cnb = 2.002891 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 2.004732 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_02.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_02.txt index a0925bfc7d..53bfed2fd7 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_02.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_02.txt @@ -13,57 +13,57 @@ Run case: case_06_02 - Alpha = 0.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 0.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = -0.00352 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.04266 - CZtot = -0.21751 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.21751 - CDtot = 0.00352 - CDvis = 0.00000 CDind = 0.0035209 - CLff = 0.21728 CDff = 0.0024567 | Trefftz - CYff = -0.00000 e = 0.6484 | Plane - + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = -0.00357 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.04109 + CZtot = -0.21886 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.21886 + CDtot = 0.00357 + CDvis = 0.00000 CDind = 0.00357 + CLff = 0.21859 CDff = 0.00251 | Trefftz + CYff = -0.00000 e = 0.6426 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 7.941208 CLb = 0.000001 - y force CY | CYa = -0.000000 CYb = -0.940388 - x' mom. Cl'| Cla = -0.000007 Clb = -0.250944 - y mom. Cm | Cma = -11.133167 Cmb = 0.000003 - z' mom. Cn'| Cna = -0.000001 Cnb = 0.342324 + z' force CL | CLa = 7.942349 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.940431 + x' mom. Cl'| Cla = -0.000001 Clb = -0.251177 + y mom. Cm | Cma = -11.133526 Cmb = 0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.342313 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000013 CLq = 36.969437 CLr = -0.000001 - y force CY | CYp = -0.268764 CYq = -0.000002 CYr = 1.154289 - x' mom. Cl'| Clp = -0.636472 Clq = -0.000040 Clr = 0.247499 - y mom. Cm | Cmp = -0.000026 Cmq =-104.676361 Cmr = -0.000002 - z' mom. Cn'| Cnp = 0.095485 Cnq = 0.000000 Cnr = -0.611531 + z' force CL | CLp = 0.000002 CLq = 36.972527 CLr = -0.000000 + y force CY | CYp = -0.268415 CYq = -0.000000 CYr = 1.154339 + x' mom. Cl'| Clp = -0.636490 Clq = -0.000006 Clr = 0.247529 + y mom. Cm | Cmp = -0.000003 Cmq =-104.687897 Cmr = -0.000000 + z' mom. Cn'| Cnp = 0.095320 Cnq = -0.000000 Cnr = -0.611522 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000780 CLd2 = 0.038058 CLd3 = -0.000000 CLd4 = 0.016578 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000426 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000781 CLd2 = 0.038055 CLd3 = -0.000000 CLd4 = 0.016581 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000429 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002582 Cld4 = -0.000000 - y mom. Cm | Cmd1 = -0.000058 Cmd2 = -0.036551 Cmd3 = 0.000000 Cmd4 = -0.082483 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000046 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000435 CDffd3 = -0.000000 CDffd4 = 0.000126 - span eff. | ed1 = -0.001788 ed2 = 0.112020 ed3 = 0.000000 ed4 = 0.065311 - - + y mom. Cm | Cmd1 = -0.000056 Cmd2 = -0.036544 Cmd3 = 0.000000 Cmd4 = -0.082495 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000051 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000011 CDffd2 = 0.000435 CDffd3 = -0.000000 CDffd4 = 0.000128 + span eff. | ed1 = -0.001793 ed2 = 0.112044 ed3 = 0.000000 ed4 = 0.064424 + + - Neutral point Xnp = 21.247131 + Neutral point Xnp = 21.246469 - Clb Cnr / Clr Cnb = 1.811269 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.812764 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_03.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_03.txt index a6e469f02c..31d12a70d8 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_03.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_03.txt @@ -13,57 +13,57 @@ Run case: case_06_03 - Alpha = 2.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 2.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.00599 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = -0.00000 Cmtot = -0.43203 - CZtot = -0.49464 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.49455 - CDtot = 0.01128 - CDvis = 0.00000 CDind = 0.0112786 - CLff = 0.49382 CDff = 0.0092730 | Trefftz - CYff = -0.00000 e = 0.8874 | Plane - + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.00597 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -0.43046 + CZtot = -0.49603 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.49594 + CDtot = 0.01135 + CDvis = 0.00000 CDind = 0.01135 + CLff = 0.49513 CDff = 0.00935 | Trefftz + CYff = -0.00000 e = 0.8844 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 7.927197 CLb = 0.000001 - y force CY | CYa = 0.000000 CYb = -0.950635 - x' mom. Cl'| Cla = -0.000007 Clb = -0.273578 - y mom. Cm | Cma = -11.167062 Cmb = 0.000002 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.350946 + z' force CL | CLa = 7.928359 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.950671 + x' mom. Cl'| Cla = -0.000001 Clb = -0.273813 + y mom. Cm | Cma = -11.166652 Cmb = 0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.350944 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000013 CLq = 37.015728 CLr = -0.000002 - y force CY | CYp = -0.137892 CYq = -0.000002 CYr = 1.182292 - x' mom. Cl'| Clp = -0.624094 Clq = -0.000040 Clr = 0.292519 - y mom. Cm | Cmp = -0.000026 Cmq =-105.002258 Cmr = 0.000000 - z' mom. Cn'| Cnp = 0.035524 Cnq = 0.000001 Cnr = -0.629090 + z' force CL | CLp = 0.000002 CLq = 37.015701 CLr = -0.000000 + y force CY | CYp = -0.137539 CYq = -0.000000 CYr = 1.182330 + x' mom. Cl'| Clp = -0.624116 Clq = -0.000005 Clr = 0.292550 + y mom. Cm | Cmp = -0.000003 Cmq =-105.005417 Cmr = -0.000000 + z' mom. Cn'| Cnp = 0.035365 Cnq = 0.000000 Cnr = -0.629077 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000821 CLd2 = 0.037936 CLd3 = -0.000000 CLd4 = 0.016530 - y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000397 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000821 CLd2 = 0.037929 CLd3 = -0.000000 CLd4 = 0.016532 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000401 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002571 Cld4 = -0.000000 - y mom. Cm | Cmd1 = -0.000025 Cmd2 = -0.036431 Cmd3 = 0.000000 Cmd4 = -0.082343 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000008 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000023 CDffd2 = 0.001033 CDffd3 = -0.000000 CDffd4 = 0.000590 - span eff. | ed1 = -0.000532 ed2 = 0.037307 ed3 = 0.000000 ed4 = 0.002737 - - + y mom. Cm | Cmd1 = -0.000023 Cmd2 = -0.036422 Cmd3 = 0.000000 Cmd4 = -0.082351 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = -0.000013 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000023 CDffd2 = 0.001033 CDffd3 = -0.000000 CDffd4 = 0.000592 + span eff. | ed1 = -0.000538 ed2 = 0.037672 ed3 = 0.000000 ed4 = 0.002905 + + - Neutral point Xnp = 21.275734 + Neutral point Xnp = 21.274639 - Clb Cnr / Clr Cnb = 1.676485 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.677723 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_04.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_04.txt index 0d2528bb5a..809121c9d5 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_04.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_04.txt @@ -13,57 +13,57 @@ Run case: case_06_04 - Alpha = 5.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 5.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.04509 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.01593 - CZtot = -0.90750 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 0.90797 - CDtot = 0.03417 - CDvis = 0.00000 CDind = 0.0341712 - CLff = 0.90741 CDff = 0.0299864 | Trefftz - CYff = 0.00000 e = 0.9265 | Plane - + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.04515 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.01431 + CZtot = -0.90895 Cntot = -0.00000 Cn'tot = -0.00000 + + CLtot = 0.90943 + CDtot = 0.03424 + CDvis = 0.00000 CDind = 0.03424 + CLff = 0.90872 CDff = 0.03011 | Trefftz + CYff = 0.00000 e = 0.9255 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 7.854228 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.963829 - x' mom. Cl'| Cla = -0.000007 Clb = -0.306265 - y mom. Cm | Cma = -11.115914 Cmb = 0.000001 - z' mom. Cn'| Cna = -0.000000 Cnb = 0.366785 + z' force CL | CLa = 7.855483 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.963855 + x' mom. Cl'| Cla = -0.000001 Clb = -0.306501 + y mom. Cm | Cma = -11.114361 Cmb = 0.000000 + z' mom. Cn'| Cna = -0.000000 Cnb = 0.366795 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000013 CLq = 37.068428 CLr = -0.000003 - y force CY | CYp = 0.061279 CYq = -0.000003 CYr = 1.207019 - x' mom. Cl'| Clp = -0.606266 Clq = -0.000040 Clr = 0.357127 - y mom. Cm | Cmp = -0.000025 Cmq =-105.251144 Cmr = 0.000004 - z' mom. Cn'| Cnp = -0.056712 Cnq = 0.000003 Cnr = -0.651826 + z' force CL | CLp = 0.000002 CLq = 37.064129 CLr = -0.000000 + y force CY | CYp = 0.061636 CYq = -0.000000 CYr = 1.207040 + x' mom. Cl'| Clp = -0.606293 Clq = -0.000005 Clr = 0.357160 + y mom. Cm | Cmp = -0.000003 Cmq =-105.241791 Cmr = 0.000000 + z' mom. Cn'| Cnp = -0.056861 Cnq = 0.000000 Cnr = -0.651807 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.000925 CLd2 = 0.037559 CLd3 = -0.000000 CLd4 = 0.016357 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000353 CYd4 = -0.000000 + z' force CL | CLd1 = -0.000925 CLd2 = 0.037547 CLd3 = -0.000000 CLd4 = 0.016358 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000357 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002544 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000025 Cmd2 = -0.036086 Cmd3 = 0.000000 Cmd4 = -0.081756 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000049 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000042 CDffd2 = 0.001918 CDffd3 = -0.000000 CDffd4 = 0.001278 - span eff. | ed1 = -0.000262 ed2 = 0.017632 ed3 = 0.000000 ed4 = -0.006029 - - + y mom. Cm | Cmd1 = 0.000027 Cmd2 = -0.036073 Cmd3 = 0.000000 Cmd4 = -0.081760 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000044 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000042 CDffd2 = 0.001918 CDffd3 = -0.000000 CDffd4 = 0.001279 + span eff. | ed1 = -0.000263 ed2 = 0.017741 ed3 = 0.000000 ed4 = -0.005960 + + - Neutral point Xnp = 21.303581 + Neutral point Xnp = 21.301785 - Clb Cnr / Clr Cnb = 1.524035 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.524984 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_05.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_05.txt index cd27f2f65e..562bcbb7e6 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_05.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_05.txt @@ -13,57 +13,57 @@ Run case: case_06_05 - Alpha = 7.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 7.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.08754 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.40233 - CZtot = -1.17889 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.18077 - CDtot = 0.05678 - CDvis = 0.00000 CDind = 0.0567812 - CLff = 1.18182 CDff = 0.0506898 | Trefftz - CYff = 0.00000 e = 0.9298 | Plane - + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.08767 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.40064 + CZtot = -1.18038 Cntot = -0.00000 Cn'tot = 0.00000 + + CLtot = 1.18227 + CDtot = 0.05684 + CDvis = 0.00000 CDind = 0.05684 + CLff = 1.18313 CDff = 0.05084 | Trefftz + CYff = 0.00000 e = 0.9291 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 7.771417 CLb = 0.000002 - y force CY | CYa = 0.000001 CYb = -0.971159 - x' mom. Cl'| Cla = -0.000007 Clb = -0.327059 - y mom. Cm | Cma = -11.014065 Cmb = 0.000000 - z' mom. Cn'| Cna = 0.000000 Cnb = 0.379206 + z' force CL | CLa = 7.772771 CLb = 0.000000 + y force CY | CYa = -0.000000 CYb = -0.971179 + x' mom. Cl'| Cla = -0.000001 Clb = -0.327295 + y mom. Cm | Cma = -11.011756 Cmb = 0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.379225 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000012 CLq = 37.092152 CLr = -0.000005 - y force CY | CYp = 0.195025 CYq = -0.000003 CYr = 1.211870 - x' mom. Cl'| Clp = -0.595065 Clq = -0.000040 Clr = 0.398361 - y mom. Cm | Cmp = -0.000024 Cmq =-105.256813 Cmr = 0.000007 - z' mom. Cn'| Cnp = -0.119436 Cnq = 0.000004 Cnr = -0.664383 + z' force CL | CLp = 0.000002 CLq = 37.085278 CLr = -0.000000 + y force CY | CYp = 0.195384 CYq = -0.000001 CYr = 1.211879 + x' mom. Cl'| Clp = -0.595095 Clq = -0.000005 Clr = 0.398395 + y mom. Cm | Cmp = -0.000003 Cmq =-105.239098 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.119578 Cnq = 0.000001 Cnr = -0.664361 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.001022 CLd2 = 0.037179 CLd3 = -0.000000 CLd4 = 0.016176 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000323 CYd4 = -0.000000 + z' force CL | CLd1 = -0.001023 CLd2 = 0.037164 CLd3 = -0.000000 CLd4 = 0.016176 + y force CY | CYd1 = -0.000000 CYd2 = -0.000000 CYd3 = 0.000327 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002518 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000058 Cmd2 = -0.035748 Cmd3 = 0.000000 Cmd4 = -0.081117 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000086 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000055 CDffd2 = 0.002495 CDffd3 = -0.000000 CDffd4 = 0.001727 - span eff. | ed1 = -0.000202 ed2 = 0.013141 ed3 = 0.000000 ed4 = -0.006045 - - + y mom. Cm | Cmd1 = 0.000061 Cmd2 = -0.035732 Cmd3 = 0.000000 Cmd4 = -0.081118 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000082 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000055 CDffd2 = 0.002495 CDffd3 = -0.000000 CDffd4 = 0.001729 + span eff. | ed1 = -0.000202 ed2 = 0.013201 ed3 = 0.000000 ed4 = -0.006005 + + - Neutral point Xnp = 21.311945 + Neutral point Xnp = 21.309643 - Clb Cnr / Clr Cnb = 1.438439 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.439235 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_06.txt b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_06.txt index 1f14989389..08e1dd3cdf 100644 --- a/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_06.txt +++ b/regression/scripts/AVL/avl_files/stability_axis_derivatives_case_06_06.txt @@ -13,57 +13,57 @@ Run case: case_06_06 - Alpha = 10.00000 pb/2V = -0.00000 p'b/2V = -0.00000 + Alpha = 10.00000 pb/2V = 0.00000 p'b/2V = 0.00000 Beta = 0.00000 qc/2V = 0.00000 - Mach = 0.850 rb/2V = -0.00000 r'b/2V = -0.00000 - - CXtot = 0.17526 Cltot = -0.00000 Cl'tot = -0.00000 - CYtot = 0.00000 Cmtot = -1.97292 - CZtot = -1.57691 Cntot = -0.00000 Cn'tot = -0.00000 - - CLtot = 1.58338 - CDtot = 0.10123 - CDvis = 0.00000 CDind = 0.1012270 - CLff = 1.59063 CDff = 0.0918345 | Trefftz - CYff = 0.00000 e = 0.9297 | Plane - + Mach = 0.850 rb/2V = 0.00000 r'b/2V = 0.00000 + + CXtot = 0.17551 Cltot = -0.00000 Cl'tot = -0.00000 + CYtot = -0.00000 Cmtot = -1.97108 + CZtot = -1.57846 Cntot = -0.00000 Cn'tot = 0.00000 + + CLtot = 1.58496 + CDtot = 0.10125 + CDvis = 0.00000 CDind = 0.10125 + CLff = 1.59194 CDff = 0.09202 | Trefftz + CYff = 0.00000 e = 0.9293 | Plane + slat = 0.00000 flap = 0.00000 aileron = 0.00000 elevator = 0.00000 - + --------------------------------------------------------------- Stability-axis derivatives... alpha beta ---------------- ---------------- - z' force CL | CLa = 7.597475 CLb = 0.000002 - y force CY | CYa = 0.000002 CYb = -0.979934 - x' mom. Cl'| Cla = -0.000007 Clb = -0.356499 - y mom. Cm | Cma = -10.760908 Cmb = -0.000001 - z' mom. Cn'| Cna = 0.000001 Cnb = 0.400481 + z' force CL | CLa = 7.599035 CLb = 0.000000 + y force CY | CYa = 0.000000 CYb = -0.979943 + x' mom. Cl'| Cla = -0.000001 Clb = -0.356734 + y mom. Cm | Cma = -10.757487 Cmb = 0.000000 + z' mom. Cn'| Cna = 0.000000 Cnb = 0.400512 roll rate p' pitch rate q' yaw rate r' ---------------- ---------------- ---------------- - z' force CL | CLp = 0.000012 CLq = 37.110325 CLr = -0.000006 - y force CY | CYp = 0.395465 CYq = -0.000003 CYr = 1.201636 - x' mom. Cl'| Clp = -0.579574 Clq = -0.000039 Clr = 0.457686 - y mom. Cm | Cmp = -0.000023 Cmq =-105.024918 Cmr = 0.000011 - z' mom. Cn'| Cnp = -0.214827 Cnq = 0.000006 Cnr = -0.679033 + z' force CL | CLp = 0.000001 CLq = 37.100048 CLr = -0.000001 + y force CY | CYp = 0.395824 CYq = -0.000001 CYr = 1.201627 + x' mom. Cl'| Clp = -0.579606 Clq = -0.000005 Clr = 0.457722 + y mom. Cm | Cmp = -0.000003 Cmq =-104.994728 Cmr = 0.000001 + z' mom. Cn'| Cnp = -0.214959 Cnq = 0.000001 Cnr = -0.679007 slat d1 flap d2 aileron d3 elevator d4 ---------------- ---------------- ---------------- ---------------- - z' force CL | CLd1 = -0.001209 CLd2 = 0.036426 CLd3 = -0.000000 CLd4 = 0.015810 - y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000277 CYd4 = -0.000000 + z' force CL | CLd1 = -0.001209 CLd2 = 0.036406 CLd3 = -0.000000 CLd4 = 0.015809 + y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000281 CYd4 = -0.000000 x' mom. Cl'| Cld1 = 0.000000 Cld2 = -0.000000 Cld3 = 0.002468 Cld4 = -0.000000 - y mom. Cm | Cmd1 = 0.000108 Cmd2 = -0.035081 Cmd3 = 0.000000 Cmd4 = -0.079795 - z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000141 Cnd4 = 0.000000 - Trefftz drag| CDffd1 = -0.000073 CDffd2 = 0.003333 CDffd3 = -0.000000 CDffd4 = 0.002382 - span eff. | ed1 = -0.000151 ed2 = 0.009528 ed3 = 0.000000 ed4 = -0.005271 - - + y mom. Cm | Cmd1 = 0.000111 Cmd2 = -0.035061 Cmd3 = 0.000000 Cmd4 = -0.079791 + z' mom. Cn'| Cnd1 = 0.000000 Cnd2 = -0.000000 Cnd3 = 0.000136 Cnd4 = 0.000000 + Trefftz drag| CDffd1 = -0.000073 CDffd2 = 0.003333 CDffd3 = -0.000000 CDffd4 = 0.002383 + span eff. | ed1 = -0.000151 ed2 = 0.009558 ed3 = 0.000000 ed4 = -0.005250 + + - Neutral point Xnp = 21.308247 + Neutral point Xnp = 21.305107 - Clb Cnr / Clr Cnb = 1.320685 ( > 1 if spirally stable ) + Clb Cnr / Clr Cnb = 1.321298 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_01_01.txt b/regression/scripts/AVL/avl_files/strip_forces_case_01_01.txt index 6d346411bf..215346d8ab 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_01_01.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_01_01.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00858 Clsurf = 0.00261 - CYsurf = 0.00015 Cmsurf = 0.00398 - CDsurf = 0.00038 Cnsurf = -0.00020 + CLsurf = 0.00919 Clsurf = 0.00255 + CYsurf = 0.00012 Cmsurf = 0.00365 + CDsurf = 0.00038 Cnsurf = -0.00019 CDisurf = 0.00038 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01669 CDsurf = 0.00074 + CLsurf = 0.01788 CDsurf = 0.00074 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 0.7119 0.0123 0.1190 0.0925 0.0170 0.0000 -0.0042 -0.0221 0.295 - 2 0.1025 7.6885 1.0492 0.7009 0.0115 0.1176 0.0914 0.0044 0.0000 -0.0042 -0.0219 0.296 - 3 0.2837 7.5620 1.7073 0.6964 0.0098 0.1187 0.0923 0.0034 0.0000 -0.0039 -0.0219 0.292 - 4 0.5530 7.3741 2.3052 0.6859 0.0074 0.1199 0.0932 0.0030 0.0000 -0.0035 -0.0217 0.288 - 5 0.9075 7.1267 2.8223 0.6647 0.0050 0.1202 0.0934 0.0024 0.0000 -0.0033 -0.0216 0.285 - 6 1.3432 6.8226 3.2414 0.6291 0.0058 0.1188 0.0923 0.0019 0.0000 -0.0033 -0.0214 0.286 - 7 1.8554 6.4651 3.5491 0.5762 0.0156 0.1148 0.0892 0.0014 0.0000 -0.0036 -0.0211 0.291 - 8 2.4386 6.0582 3.7368 0.5032 0.0230 0.1070 0.0831 0.0007 0.0000 -0.0045 -0.0205 0.304 - 9 3.0862 5.6062 3.8005 0.4115 0.0156 0.0945 0.0735 0.0002 0.0000 -0.0059 -0.0197 0.330 - 10 3.7613 5.1351 3.4440 0.3102 0.0058 0.0778 0.0604 -0.0002 0.0000 -0.0081 -0.0188 0.383 - 11 4.4532 4.6522 3.3149 0.2061 -0.0026 0.0570 0.0443 -0.0003 0.0000 -0.0113 -0.0182 0.504 - 12 5.1831 4.1429 3.0930 0.0989 -0.0129 0.0307 0.0239 -0.0003 0.0000 -0.0157 -0.0177 0.908 - 13 6.0123 3.7903 3.4706 0.0071 -0.0178 0.0023 0.0019 -0.0001 0.0000 -0.0194 -0.0177 - 14 6.9353 3.6075 3.3775 -0.0526 -0.0136 -0.0177 -0.0146 0.0001 0.0000 -0.0201 -0.0146 - 15 7.8737 3.4215 3.2389 -0.0940 -0.0101 -0.0334 -0.0275 0.0002 0.0000 -0.0202 -0.0119 -0.485 - 16 8.8172 3.2345 3.0619 -0.1225 -0.0077 -0.0460 -0.0379 0.0003 0.0000 -0.0202 -0.0096 -0.283 - 17 9.7556 3.0486 2.8543 -0.1414 -0.0064 -0.0563 -0.0464 0.0003 0.0000 -0.0202 -0.0077 -0.185 - 18 10.6786 2.8657 2.6240 -0.1528 -0.0060 -0.0648 -0.0533 0.0003 0.0000 -0.0202 -0.0062 -0.128 - 19 11.5760 2.6879 2.3787 -0.1585 -0.0058 -0.0716 -0.0590 0.0003 0.0000 -0.0202 -0.0049 -0.092 - 20 12.4328 2.5181 2.1010 -0.1595 -0.0059 -0.0769 -0.0634 0.0002 0.0000 -0.0202 -0.0040 -0.069 - 21 13.2400 2.3582 1.8520 -0.1569 -0.0060 -0.0808 -0.0666 0.0002 0.0000 -0.0203 -0.0034 -0.055 - 22 13.9941 2.2087 1.6074 -0.1511 -0.0064 -0.0831 -0.0685 0.0002 0.0000 -0.0204 -0.0031 -0.048 - 23 14.6868 2.0715 1.3716 -0.1423 -0.0069 -0.0834 -0.0687 0.0002 0.0000 -0.0207 -0.0032 -0.051 - 24 15.3105 1.9479 1.1479 -0.1301 -0.0075 -0.0811 -0.0668 0.0001 0.0000 -0.0209 -0.0039 -0.063 - 25 15.8583 1.8393 0.9381 -0.1143 -0.0079 -0.0754 -0.0622 0.0001 0.0000 -0.0209 -0.0049 -0.086 - 26 16.3244 1.7470 0.7427 -0.0948 -0.0079 -0.0659 -0.0543 0.0001 0.0000 -0.0193 -0.0051 -0.105 - 27 16.6722 1.4928 0.4131 -0.0736 -0.0077 -0.1626 -0.0493 -0.0006 0.0000 -0.0151 -0.0015 -0.056 - 28 16.9098 1.1466 0.2292 -0.0521 -0.0064 -0.1498 -0.0455 -0.0009 0.0000 -0.0161 -0.0024 -0.104 - 29 17.0696 0.9138 0.1104 -0.0306 -0.0045 -0.1105 -0.0335 -0.0013 0.0000 -0.0150 -0.0032 -0.198 - 30 17.1499 0.7967 0.0322 -0.0100 -0.0034 -0.0418 -0.0127 -0.0022 0.0000 -0.0072 -0.0019 -0.316 + 1 0.0114 7.7520 0.3539 0.7274 0.0122 0.1216 0.0945 0.0168 0.0000 -0.0055 -0.0235 0.308 + 2 0.1025 7.6885 1.0491 0.7161 0.0115 0.1201 0.0933 0.0044 0.0000 -0.0054 -0.0233 0.308 + 3 0.2837 7.5620 1.7073 0.7118 0.0101 0.1213 0.0943 0.0035 0.0000 -0.0051 -0.0233 0.305 + 4 0.5530 7.3741 2.3052 0.7014 0.0079 0.1226 0.0953 0.0029 0.0000 -0.0048 -0.0232 0.300 + 5 0.9075 7.1267 2.8223 0.6803 0.0056 0.1230 0.0956 0.0025 0.0000 -0.0046 -0.0231 0.298 + 6 1.3432 6.8226 3.2414 0.6444 0.0064 0.1217 0.0946 0.0019 0.0000 -0.0045 -0.0229 0.298 + 7 1.8554 6.4651 3.5491 0.5905 0.0162 0.1176 0.0914 0.0012 0.0000 -0.0048 -0.0225 0.302 + 8 2.4386 6.0582 3.7368 0.5168 0.0236 0.1099 0.0854 0.0007 0.0000 -0.0055 -0.0218 0.314 + 9 3.0862 5.6062 3.8005 0.4242 0.0164 0.0974 0.0757 0.0002 0.0000 -0.0067 -0.0208 0.339 + 10 3.7613 5.1351 3.4440 0.3206 0.0064 0.0804 0.0625 -0.0001 0.0000 -0.0085 -0.0196 0.387 + 11 4.4532 4.6522 3.3149 0.2132 -0.0027 0.0590 0.0458 -0.0003 0.0000 -0.0111 -0.0183 0.492 + 12 5.1831 4.1429 3.0930 0.1027 -0.0135 0.0319 0.0248 -0.0003 0.0000 -0.0148 -0.0171 0.845 + 13 6.0123 3.7903 3.4706 0.0095 -0.0182 0.0030 0.0025 -0.0001 0.0000 -0.0180 -0.0166 + 14 6.9353 3.6075 3.3775 -0.0506 -0.0139 -0.0170 -0.0140 0.0001 0.0000 -0.0185 -0.0134 + 15 7.8737 3.4215 3.2389 -0.0923 -0.0102 -0.0328 -0.0270 0.0002 0.0000 -0.0186 -0.0106 -0.441 + 16 8.8172 3.2345 3.0619 -0.1211 -0.0078 -0.0454 -0.0374 0.0003 0.0000 -0.0186 -0.0083 -0.248 + 17 9.7556 3.0486 2.8543 -0.1401 -0.0065 -0.0558 -0.0460 0.0003 0.0000 -0.0186 -0.0064 -0.155 + 18 10.6786 2.8657 2.6239 -0.1517 -0.0060 -0.0643 -0.0530 0.0003 0.0000 -0.0186 -0.0048 -0.101 + 19 11.5760 2.6879 2.3787 -0.1576 -0.0059 -0.0712 -0.0586 0.0003 0.0000 -0.0186 -0.0036 -0.067 + 20 12.4328 2.5181 2.1010 -0.1588 -0.0059 -0.0766 -0.0631 0.0003 0.0000 -0.0186 -0.0026 -0.045 + 21 13.2400 2.3582 1.8520 -0.1563 -0.0061 -0.0805 -0.0663 0.0002 0.0000 -0.0187 -0.0020 -0.032 + 22 13.9941 2.2087 1.6074 -0.1507 -0.0064 -0.0828 -0.0682 0.0002 0.0000 -0.0188 -0.0017 -0.026 + 23 14.6868 2.0715 1.3716 -0.1420 -0.0069 -0.0832 -0.0686 0.0002 0.0000 -0.0191 -0.0018 -0.028 + 24 15.3105 1.9479 1.1479 -0.1300 -0.0075 -0.0810 -0.0668 0.0001 0.0000 -0.0193 -0.0025 -0.040 + 25 15.8583 1.8393 0.9381 -0.1143 -0.0079 -0.0755 -0.0622 0.0001 0.0000 -0.0193 -0.0034 -0.060 + 26 16.3244 1.7470 0.7427 -0.0952 -0.0082 -0.0662 -0.0545 0.0001 0.0000 -0.0177 -0.0037 -0.074 + 27 16.6722 1.4928 0.4131 -0.0740 -0.0080 -0.1635 -0.0496 -0.0005 0.0000 -0.0138 -0.0008 -0.029 + 28 16.9098 1.1466 0.2292 -0.0522 -0.0065 -0.1502 -0.0456 -0.0008 0.0000 -0.0151 -0.0019 -0.081 + 29 17.0696 0.9138 0.1104 -0.0306 -0.0043 -0.1105 -0.0335 -0.0013 0.0000 -0.0144 -0.0030 -0.180 + 30 17.1499 0.7967 0.0322 -0.0100 -0.0027 -0.0415 -0.0126 -0.0021 0.0000 -0.0070 -0.0019 -0.306 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00858 Clsurf = -0.00261 - CYsurf = -0.00015 Cmsurf = 0.00398 - CDsurf = 0.00038 Cnsurf = 0.00020 + CLsurf = 0.00919 Clsurf = -0.00255 + CYsurf = -0.00012 Cmsurf = 0.00365 + CDsurf = 0.00038 Cnsurf = 0.00019 CDisurf = 0.00038 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01669 CDsurf = 0.00074 + CLsurf = 0.01788 CDsurf = 0.00074 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 0.7119 0.0122 0.1190 0.0925 0.0170 0.0000 -0.0042 0.0221 0.295 - 32 -0.1025 7.6885 1.0492 0.7009 0.0114 0.1176 0.0914 0.0044 0.0000 -0.0042 0.0219 0.296 - 33 -0.2837 7.5620 1.7073 0.6964 0.0098 0.1187 0.0923 0.0034 0.0000 -0.0039 0.0219 0.292 - 34 -0.5530 7.3741 2.3052 0.6859 0.0074 0.1199 0.0932 0.0030 0.0000 -0.0035 0.0217 0.288 - 35 -0.9075 7.1267 2.8223 0.6647 0.0050 0.1202 0.0934 0.0024 0.0000 -0.0033 0.0216 0.285 - 36 -1.3432 6.8226 3.2414 0.6290 0.0058 0.1188 0.0923 0.0019 0.0000 -0.0033 0.0214 0.286 - 37 -1.8554 6.4651 3.5491 0.5762 0.0156 0.1148 0.0892 0.0014 0.0000 -0.0036 0.0211 0.291 - 38 -2.4386 6.0582 3.7368 0.5032 0.0230 0.1070 0.0831 0.0007 0.0000 -0.0045 0.0205 0.304 - 39 -3.0862 5.6062 3.8005 0.4115 0.0156 0.0945 0.0735 0.0002 0.0000 -0.0059 0.0197 0.330 - 40 -3.7613 5.1351 3.4440 0.3102 0.0058 0.0778 0.0604 -0.0002 0.0000 -0.0081 0.0188 0.383 - 41 -4.4532 4.6522 3.3149 0.2061 -0.0026 0.0570 0.0443 -0.0003 0.0000 -0.0113 0.0182 0.504 - 42 -5.1831 4.1429 3.0930 0.0989 -0.0129 0.0307 0.0239 -0.0003 0.0000 -0.0157 0.0177 0.908 - 43 -6.0123 3.7903 3.4706 0.0071 -0.0178 0.0023 0.0019 -0.0001 0.0000 -0.0194 0.0177 - 44 -6.9353 3.6075 3.3775 -0.0526 -0.0136 -0.0177 -0.0146 0.0001 0.0000 -0.0201 0.0146 - 45 -7.8737 3.4215 3.2389 -0.0940 -0.0101 -0.0334 -0.0275 0.0002 0.0000 -0.0202 0.0119 -0.485 - 46 -8.8172 3.2345 3.0619 -0.1225 -0.0077 -0.0460 -0.0379 0.0003 0.0000 -0.0202 0.0096 -0.283 - 47 -9.7556 3.0486 2.8543 -0.1414 -0.0064 -0.0563 -0.0464 0.0003 0.0000 -0.0202 0.0077 -0.185 - 48 -10.6786 2.8657 2.6240 -0.1528 -0.0060 -0.0648 -0.0533 0.0003 0.0000 -0.0202 0.0062 -0.128 - 49 -11.5760 2.6879 2.3787 -0.1585 -0.0058 -0.0716 -0.0590 0.0003 0.0000 -0.0202 0.0049 -0.092 - 50 -12.4328 2.5181 2.1010 -0.1595 -0.0059 -0.0769 -0.0634 0.0002 0.0000 -0.0202 0.0040 -0.069 - 51 -13.2400 2.3582 1.8520 -0.1569 -0.0060 -0.0808 -0.0666 0.0002 0.0000 -0.0203 0.0034 -0.055 - 52 -13.9941 2.2087 1.6074 -0.1511 -0.0064 -0.0831 -0.0685 0.0002 0.0000 -0.0204 0.0031 -0.048 - 53 -14.6868 2.0715 1.3716 -0.1423 -0.0069 -0.0834 -0.0687 0.0002 0.0000 -0.0207 0.0032 -0.051 - 54 -15.3105 1.9479 1.1479 -0.1301 -0.0075 -0.0811 -0.0668 0.0001 0.0000 -0.0209 0.0039 -0.063 - 55 -15.8583 1.8393 0.9381 -0.1143 -0.0079 -0.0754 -0.0622 0.0001 0.0000 -0.0209 0.0049 -0.086 - 56 -16.3244 1.7470 0.7427 -0.0948 -0.0079 -0.0659 -0.0543 0.0001 0.0000 -0.0193 0.0051 -0.105 - 57 -16.6722 1.4928 0.4131 -0.0736 -0.0077 -0.1626 -0.0493 -0.0006 0.0000 -0.0151 0.0015 -0.056 - 58 -16.9098 1.1466 0.2292 -0.0521 -0.0064 -0.1498 -0.0455 -0.0009 0.0000 -0.0161 0.0024 -0.104 - 59 -17.0696 0.9138 0.1104 -0.0306 -0.0045 -0.1105 -0.0335 -0.0013 0.0000 -0.0150 0.0032 -0.198 - 60 -17.1499 0.7967 0.0322 -0.0100 -0.0034 -0.0418 -0.0127 -0.0022 0.0000 -0.0072 0.0019 -0.316 + 31 -0.0114 7.7520 0.3539 0.7274 0.0122 0.1216 0.0945 0.0168 0.0000 -0.0055 0.0235 0.308 + 32 -0.1025 7.6885 1.0491 0.7161 0.0115 0.1201 0.0933 0.0044 0.0000 -0.0054 0.0233 0.308 + 33 -0.2837 7.5620 1.7073 0.7118 0.0101 0.1213 0.0943 0.0035 0.0000 -0.0051 0.0233 0.305 + 34 -0.5530 7.3741 2.3052 0.7014 0.0079 0.1226 0.0953 0.0029 0.0000 -0.0048 0.0232 0.300 + 35 -0.9075 7.1267 2.8223 0.6803 0.0056 0.1230 0.0956 0.0025 0.0000 -0.0046 0.0231 0.298 + 36 -1.3432 6.8226 3.2414 0.6444 0.0064 0.1217 0.0946 0.0019 0.0000 -0.0045 0.0229 0.298 + 37 -1.8554 6.4651 3.5491 0.5905 0.0162 0.1176 0.0914 0.0012 0.0000 -0.0048 0.0225 0.302 + 38 -2.4386 6.0582 3.7368 0.5168 0.0236 0.1099 0.0854 0.0007 0.0000 -0.0055 0.0218 0.314 + 39 -3.0862 5.6062 3.8005 0.4242 0.0164 0.0974 0.0757 0.0002 0.0000 -0.0067 0.0208 0.339 + 40 -3.7613 5.1351 3.4440 0.3206 0.0064 0.0804 0.0625 -0.0001 0.0000 -0.0085 0.0196 0.387 + 41 -4.4532 4.6522 3.3149 0.2132 -0.0027 0.0590 0.0458 -0.0003 0.0000 -0.0111 0.0183 0.492 + 42 -5.1831 4.1429 3.0930 0.1027 -0.0135 0.0319 0.0248 -0.0003 0.0000 -0.0148 0.0171 0.845 + 43 -6.0123 3.7903 3.4706 0.0095 -0.0182 0.0030 0.0025 -0.0001 0.0000 -0.0180 0.0166 + 44 -6.9353 3.6075 3.3775 -0.0506 -0.0139 -0.0170 -0.0140 0.0001 0.0000 -0.0185 0.0134 + 45 -7.8737 3.4215 3.2389 -0.0923 -0.0102 -0.0328 -0.0270 0.0002 0.0000 -0.0186 0.0106 -0.441 + 46 -8.8172 3.2345 3.0619 -0.1211 -0.0078 -0.0454 -0.0374 0.0003 0.0000 -0.0186 0.0083 -0.248 + 47 -9.7556 3.0486 2.8543 -0.1401 -0.0065 -0.0558 -0.0460 0.0003 0.0000 -0.0186 0.0064 -0.155 + 48 -10.6786 2.8657 2.6239 -0.1517 -0.0060 -0.0643 -0.0530 0.0003 0.0000 -0.0186 0.0048 -0.101 + 49 -11.5760 2.6879 2.3787 -0.1576 -0.0059 -0.0712 -0.0586 0.0003 0.0000 -0.0186 0.0036 -0.067 + 50 -12.4328 2.5181 2.1010 -0.1588 -0.0059 -0.0766 -0.0631 0.0003 0.0000 -0.0186 0.0026 -0.045 + 51 -13.2400 2.3582 1.8520 -0.1563 -0.0061 -0.0805 -0.0663 0.0002 0.0000 -0.0187 0.0020 -0.032 + 52 -13.9941 2.2087 1.6074 -0.1507 -0.0064 -0.0828 -0.0682 0.0002 0.0000 -0.0188 0.0017 -0.026 + 53 -14.6868 2.0715 1.3716 -0.1420 -0.0069 -0.0832 -0.0686 0.0002 0.0000 -0.0191 0.0018 -0.028 + 54 -15.3105 1.9479 1.1479 -0.1300 -0.0075 -0.0810 -0.0668 0.0001 0.0000 -0.0193 0.0025 -0.040 + 55 -15.8583 1.8393 0.9381 -0.1143 -0.0079 -0.0755 -0.0622 0.0001 0.0000 -0.0193 0.0034 -0.060 + 56 -16.3244 1.7470 0.7427 -0.0952 -0.0082 -0.0662 -0.0545 0.0001 0.0000 -0.0177 0.0037 -0.074 + 57 -16.6722 1.4928 0.4131 -0.0740 -0.0080 -0.1635 -0.0496 -0.0005 0.0000 -0.0138 0.0008 -0.029 + 58 -16.9098 1.1466 0.2292 -0.0522 -0.0065 -0.1502 -0.0456 -0.0008 0.0000 -0.0151 0.0019 -0.081 + 59 -17.0696 0.9138 0.1104 -0.0306 -0.0043 -0.1105 -0.0335 -0.0013 0.0000 -0.0144 0.0030 -0.180 + 60 -17.1499 0.7967 0.0322 -0.0100 -0.0027 -0.0415 -0.0126 -0.0021 0.0000 -0.0070 0.0019 -0.306 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02774 Clsurf = 0.00270 - CYsurf = 0.00446 Cmsurf = 0.13303 - CDsurf = 0.00011 Cnsurf = -0.00275 - CDisurf = 0.00011 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02788 Clsurf = 0.00272 + CYsurf = 0.00449 Cmsurf = 0.13367 + CDsurf = 0.00010 Cnsurf = -0.00276 + CDisurf = 0.00010 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.16911 CDsurf = 0.00065 + CLsurf = -0.16995 CDsurf = 0.00061 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.5731 -0.0206 -0.1698 -0.1325 0.0525 0.0000 0.0079 0.0347 0.310 - 62 0.0418 4.2566 0.2392 -0.6468 -0.0211 -0.1947 -0.1518 0.0063 0.0000 0.0074 0.0380 0.299 - 63 0.1156 4.2274 0.3930 -0.6523 -0.0215 -0.1978 -0.1543 0.0034 0.0000 0.0070 0.0381 0.295 - 64 0.2254 4.1839 0.5386 -0.6540 -0.0217 -0.2004 -0.1563 0.0025 0.0000 0.0061 0.0378 0.289 - 65 0.3698 4.1268 0.6730 -0.6542 -0.0218 -0.2033 -0.1585 0.0021 0.0000 0.0051 0.0374 0.282 - 66 0.5474 4.0565 0.7936 -0.6538 -0.0215 -0.2067 -0.1612 0.0018 0.0000 0.0041 0.0371 0.275 - 67 0.7617 3.9717 0.9441 -0.6515 -0.0207 -0.2104 -0.1641 0.0013 0.0000 0.0031 0.0368 0.269 - 68 1.0116 3.8728 1.0344 -0.6471 -0.0193 -0.2143 -0.1671 0.0010 0.0000 0.0022 0.0367 0.263 - 69 1.2891 3.7630 1.1046 -0.6411 -0.0173 -0.2186 -0.1704 0.0007 0.0000 0.0014 0.0367 0.258 - 70 1.5912 3.6435 1.1542 -0.6316 -0.0149 -0.2224 -0.1734 0.0005 0.0000 0.0007 0.0368 0.254 - 71 1.9146 3.5155 1.1831 -0.6190 -0.0124 -0.2259 -0.1762 0.0003 0.0000 0.0003 0.0370 0.251 - 72 2.2558 3.3805 1.1921 -0.6036 -0.0105 -0.2291 -0.1787 0.0001 0.0000 -0.0001 0.0372 0.249 - 73 2.6109 3.2400 1.1821 -0.5848 -0.0094 -0.2316 -0.1806 -0.0001 0.0000 -0.0004 0.0374 0.248 - 74 2.9762 3.0955 1.1548 -0.5630 -0.0090 -0.2334 -0.1820 -0.0001 0.0000 -0.0006 0.0375 0.247 - 75 3.3476 2.9485 1.1122 -0.5386 -0.0092 -0.2344 -0.1828 -0.0002 0.0000 -0.0007 0.0375 0.246 - 76 3.7210 2.8008 1.0564 -0.5119 -0.0097 -0.2345 -0.1829 -0.0002 0.0000 -0.0009 0.0375 0.245 - 77 4.0924 2.6538 0.9900 -0.4838 -0.0103 -0.2339 -0.1824 -0.0002 0.0000 -0.0010 0.0372 0.245 - 78 4.4577 2.5093 0.9155 -0.4546 -0.0111 -0.2324 -0.1813 -0.0002 0.0000 -0.0011 0.0369 0.244 - 79 4.8128 2.3687 0.8353 -0.4248 -0.0120 -0.2301 -0.1795 -0.0002 0.0000 -0.0014 0.0363 0.242 - 80 5.1540 2.2338 0.7518 -0.3947 -0.0130 -0.2267 -0.1768 -0.0001 0.0000 -0.0017 0.0355 0.240 - 81 5.4774 2.1058 0.6671 -0.3643 -0.0142 -0.2219 -0.1731 -0.0001 0.0000 -0.0022 0.0343 0.238 - 82 5.7795 1.9862 0.5830 -0.3337 -0.0155 -0.2155 -0.1681 -0.0002 0.0000 -0.0028 0.0327 0.233 - 83 6.0570 1.8764 0.5012 -0.3025 -0.0171 -0.2068 -0.1613 -0.0002 0.0000 -0.0037 0.0306 0.227 - 84 6.3069 1.7776 0.4225 -0.2707 -0.0188 -0.1954 -0.1524 -0.0002 0.0000 -0.0047 0.0278 0.219 - 85 6.5264 1.6907 0.3478 -0.2375 -0.0204 -0.1803 -0.1406 -0.0002 0.0000 -0.0059 0.0244 0.208 - 86 6.7314 1.6096 0.3326 -0.2011 -0.0221 -0.1604 -0.1250 -0.0003 0.0000 -0.0070 0.0202 0.194 - 87 6.9144 1.5372 0.2507 -0.1598 -0.0237 -0.1334 -0.1040 -0.0004 0.0000 -0.0077 0.0152 0.176 - 88 7.0535 1.4822 0.1746 -0.1161 -0.0250 -0.1006 -0.0784 -0.0005 0.0000 -0.0074 0.0101 0.156 - 89 7.1471 1.4451 0.1029 -0.0705 -0.0258 -0.0626 -0.0488 -0.0005 0.0000 -0.0055 0.0056 0.138 - 90 7.1941 1.4265 0.0340 -0.0236 -0.0263 -0.0213 -0.0166 -0.0005 0.0000 -0.0020 0.0017 0.128 + 61 0.0047 4.2713 0.0803 -0.5761 -0.0205 -0.1707 -0.1331 0.0531 0.0000 0.0079 0.0348 0.310 + 62 0.0418 4.2566 0.2392 -0.6506 -0.0210 -0.1958 -0.1527 0.0064 0.0000 0.0075 0.0383 0.299 + 63 0.1156 4.2274 0.3930 -0.6564 -0.0214 -0.1990 -0.1552 0.0034 0.0000 0.0070 0.0383 0.295 + 64 0.2254 4.1839 0.5386 -0.6580 -0.0217 -0.2017 -0.1573 0.0025 0.0000 0.0062 0.0381 0.289 + 65 0.3698 4.1268 0.6730 -0.6581 -0.0217 -0.2045 -0.1595 0.0021 0.0000 0.0051 0.0377 0.282 + 66 0.5474 4.0565 0.7936 -0.6574 -0.0214 -0.2079 -0.1621 0.0017 0.0000 0.0041 0.0373 0.275 + 67 0.7617 3.9717 0.9441 -0.6552 -0.0206 -0.2116 -0.1650 0.0014 0.0000 0.0031 0.0370 0.269 + 68 1.0116 3.8728 1.0344 -0.6515 -0.0192 -0.2158 -0.1683 0.0009 0.0000 0.0021 0.0370 0.263 + 69 1.2891 3.7630 1.1046 -0.6448 -0.0172 -0.2198 -0.1714 0.0007 0.0000 0.0014 0.0370 0.258 + 70 1.5912 3.6435 1.1542 -0.6353 -0.0148 -0.2237 -0.1745 0.0004 0.0000 0.0007 0.0370 0.254 + 71 1.9146 3.5155 1.1831 -0.6228 -0.0123 -0.2273 -0.1773 0.0002 0.0000 0.0002 0.0372 0.251 + 72 2.2558 3.3805 1.1921 -0.6072 -0.0104 -0.2304 -0.1797 0.0000 0.0000 -0.0001 0.0374 0.249 + 73 2.6109 3.2400 1.1821 -0.5880 -0.0093 -0.2329 -0.1816 -0.0001 0.0000 -0.0004 0.0376 0.248 + 74 2.9762 3.0955 1.1548 -0.5659 -0.0089 -0.2345 -0.1829 -0.0001 0.0000 -0.0006 0.0377 0.247 + 75 3.3476 2.9485 1.1122 -0.5412 -0.0091 -0.2355 -0.1837 -0.0002 0.0000 -0.0007 0.0377 0.246 + 76 3.7210 2.8008 1.0564 -0.5145 -0.0096 -0.2357 -0.1838 -0.0002 0.0000 -0.0009 0.0376 0.245 + 77 4.0924 2.6538 0.9900 -0.4861 -0.0102 -0.2350 -0.1833 -0.0002 0.0000 -0.0010 0.0374 0.245 + 78 4.4577 2.5093 0.9155 -0.4565 -0.0110 -0.2334 -0.1820 -0.0002 0.0000 -0.0012 0.0370 0.244 + 79 4.8128 2.3687 0.8353 -0.4264 -0.0119 -0.2310 -0.1801 -0.0002 0.0000 -0.0014 0.0364 0.242 + 80 5.1540 2.2338 0.7518 -0.3960 -0.0129 -0.2275 -0.1774 -0.0002 0.0000 -0.0017 0.0356 0.240 + 81 5.4774 2.1058 0.6671 -0.3654 -0.0141 -0.2226 -0.1736 -0.0002 0.0000 -0.0022 0.0344 0.238 + 82 5.7795 1.9862 0.5830 -0.3347 -0.0155 -0.2162 -0.1686 -0.0002 0.0000 -0.0028 0.0328 0.233 + 83 6.0570 1.8764 0.5012 -0.3033 -0.0171 -0.2074 -0.1617 -0.0002 0.0000 -0.0037 0.0307 0.227 + 84 6.3069 1.7776 0.4225 -0.2712 -0.0187 -0.1958 -0.1527 -0.0002 0.0000 -0.0047 0.0279 0.219 + 85 6.5264 1.6907 0.3478 -0.2380 -0.0204 -0.1806 -0.1409 -0.0003 0.0000 -0.0059 0.0244 0.208 + 86 6.7314 1.6096 0.3326 -0.2015 -0.0221 -0.1606 -0.1253 -0.0003 0.0000 -0.0070 0.0202 0.194 + 87 6.9144 1.5372 0.2507 -0.1602 -0.0237 -0.1337 -0.1043 -0.0004 0.0000 -0.0077 0.0152 0.176 + 88 7.0535 1.4822 0.1746 -0.1163 -0.0249 -0.1007 -0.0785 -0.0005 0.0000 -0.0074 0.0101 0.156 + 89 7.1471 1.4451 0.1029 -0.0706 -0.0258 -0.0627 -0.0489 -0.0005 0.0000 -0.0055 0.0056 0.138 + 90 7.1941 1.4265 0.0340 -0.0237 -0.0263 -0.0213 -0.0166 -0.0005 0.0000 -0.0020 0.0017 0.128 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02774 Clsurf = -0.00270 - CYsurf = -0.00446 Cmsurf = 0.13302 - CDsurf = 0.00011 Cnsurf = 0.00275 - CDisurf = 0.00011 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02788 Clsurf = -0.00272 + CYsurf = -0.00449 Cmsurf = 0.13367 + CDsurf = 0.00010 Cnsurf = 0.00276 + CDisurf = 0.00010 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.16911 CDsurf = 0.00065 + CLsurf = -0.16995 CDsurf = 0.00061 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.5731 -0.0206 -0.1698 -0.1325 0.0525 0.0000 0.0079 -0.0347 0.310 - 92 -0.0418 4.2566 0.2392 -0.6468 -0.0211 -0.1947 -0.1518 0.0063 0.0000 0.0074 -0.0380 0.299 - 93 -0.1156 4.2274 0.3930 -0.6523 -0.0215 -0.1978 -0.1543 0.0034 0.0000 0.0070 -0.0381 0.295 - 94 -0.2254 4.1839 0.5386 -0.6539 -0.0217 -0.2004 -0.1563 0.0025 0.0000 0.0061 -0.0378 0.289 - 95 -0.3698 4.1268 0.6730 -0.6542 -0.0218 -0.2033 -0.1585 0.0021 0.0000 0.0051 -0.0374 0.282 - 96 -0.5474 4.0565 0.7936 -0.6537 -0.0215 -0.2067 -0.1612 0.0018 0.0000 0.0041 -0.0371 0.275 - 97 -0.7617 3.9717 0.9441 -0.6515 -0.0207 -0.2104 -0.1641 0.0013 0.0000 0.0031 -0.0368 0.269 - 98 -1.0116 3.8728 1.0344 -0.6471 -0.0193 -0.2143 -0.1671 0.0010 0.0000 0.0022 -0.0367 0.263 - 99 -1.2891 3.7630 1.1046 -0.6411 -0.0173 -0.2186 -0.1704 0.0007 0.0000 0.0014 -0.0367 0.258 - 100 -1.5912 3.6435 1.1542 -0.6316 -0.0149 -0.2224 -0.1734 0.0005 0.0000 0.0007 -0.0368 0.254 - 101 -1.9146 3.5155 1.1831 -0.6190 -0.0124 -0.2259 -0.1762 0.0003 0.0000 0.0003 -0.0370 0.251 - 102 -2.2558 3.3805 1.1921 -0.6036 -0.0105 -0.2291 -0.1787 0.0001 0.0000 -0.0001 -0.0372 0.249 - 103 -2.6109 3.2400 1.1821 -0.5848 -0.0094 -0.2316 -0.1806 -0.0001 0.0000 -0.0004 -0.0374 0.248 - 104 -2.9762 3.0955 1.1548 -0.5630 -0.0090 -0.2334 -0.1820 -0.0001 0.0000 -0.0006 -0.0375 0.247 - 105 -3.3476 2.9485 1.1122 -0.5385 -0.0092 -0.2343 -0.1828 -0.0002 0.0000 -0.0007 -0.0375 0.246 - 106 -3.7210 2.8008 1.0564 -0.5119 -0.0097 -0.2345 -0.1829 -0.0002 0.0000 -0.0009 -0.0375 0.245 - 107 -4.0924 2.6538 0.9900 -0.4838 -0.0103 -0.2339 -0.1824 -0.0002 0.0000 -0.0010 -0.0372 0.245 - 108 -4.4577 2.5093 0.9155 -0.4546 -0.0111 -0.2324 -0.1813 -0.0002 0.0000 -0.0011 -0.0369 0.244 - 109 -4.8128 2.3687 0.8353 -0.4248 -0.0120 -0.2301 -0.1795 -0.0002 0.0000 -0.0014 -0.0363 0.242 - 110 -5.1540 2.2338 0.7518 -0.3947 -0.0130 -0.2267 -0.1768 -0.0001 0.0000 -0.0017 -0.0355 0.240 - 111 -5.4774 2.1058 0.6671 -0.3642 -0.0142 -0.2219 -0.1731 -0.0001 0.0000 -0.0022 -0.0343 0.238 - 112 -5.7795 1.9862 0.5830 -0.3337 -0.0155 -0.2155 -0.1681 -0.0002 0.0000 -0.0028 -0.0327 0.233 - 113 -6.0570 1.8764 0.5012 -0.3025 -0.0171 -0.2068 -0.1613 -0.0002 0.0000 -0.0037 -0.0306 0.227 - 114 -6.3069 1.7776 0.4225 -0.2707 -0.0188 -0.1954 -0.1524 -0.0002 0.0000 -0.0047 -0.0278 0.219 - 115 -6.5264 1.6907 0.3478 -0.2375 -0.0204 -0.1803 -0.1406 -0.0002 0.0000 -0.0059 -0.0244 0.208 - 116 -6.7314 1.6096 0.3326 -0.2011 -0.0221 -0.1603 -0.1250 -0.0003 0.0000 -0.0070 -0.0202 0.194 - 117 -6.9144 1.5372 0.2507 -0.1598 -0.0237 -0.1334 -0.1040 -0.0004 0.0000 -0.0077 -0.0152 0.176 - 118 -7.0535 1.4822 0.1746 -0.1161 -0.0250 -0.1006 -0.0784 -0.0005 0.0000 -0.0074 -0.0101 0.156 - 119 -7.1471 1.4451 0.1029 -0.0705 -0.0258 -0.0626 -0.0488 -0.0005 0.0000 -0.0055 -0.0056 0.138 - 120 -7.1941 1.4265 0.0340 -0.0236 -0.0263 -0.0213 -0.0166 -0.0005 0.0000 -0.0020 -0.0017 0.128 + 91 -0.0047 4.2713 0.0803 -0.5761 -0.0205 -0.1707 -0.1331 0.0531 0.0000 0.0079 -0.0348 0.310 + 92 -0.0418 4.2566 0.2392 -0.6506 -0.0210 -0.1958 -0.1527 0.0064 0.0000 0.0075 -0.0383 0.299 + 93 -0.1156 4.2274 0.3930 -0.6564 -0.0214 -0.1990 -0.1552 0.0034 0.0000 0.0070 -0.0383 0.295 + 94 -0.2254 4.1839 0.5386 -0.6580 -0.0217 -0.2017 -0.1573 0.0025 0.0000 0.0062 -0.0381 0.289 + 95 -0.3698 4.1268 0.6730 -0.6581 -0.0217 -0.2045 -0.1595 0.0021 0.0000 0.0051 -0.0377 0.282 + 96 -0.5474 4.0565 0.7936 -0.6574 -0.0214 -0.2079 -0.1621 0.0017 0.0000 0.0041 -0.0373 0.275 + 97 -0.7617 3.9717 0.9441 -0.6552 -0.0206 -0.2116 -0.1650 0.0014 0.0000 0.0031 -0.0370 0.269 + 98 -1.0116 3.8728 1.0344 -0.6515 -0.0192 -0.2158 -0.1683 0.0009 0.0000 0.0021 -0.0370 0.263 + 99 -1.2891 3.7630 1.1046 -0.6448 -0.0172 -0.2198 -0.1714 0.0007 0.0000 0.0014 -0.0370 0.258 + 100 -1.5912 3.6435 1.1542 -0.6353 -0.0148 -0.2237 -0.1745 0.0004 0.0000 0.0007 -0.0370 0.254 + 101 -1.9146 3.5155 1.1831 -0.6228 -0.0123 -0.2273 -0.1773 0.0002 0.0000 0.0002 -0.0372 0.251 + 102 -2.2558 3.3805 1.1921 -0.6072 -0.0104 -0.2304 -0.1797 0.0000 0.0000 -0.0001 -0.0374 0.249 + 103 -2.6109 3.2400 1.1821 -0.5880 -0.0093 -0.2329 -0.1816 -0.0001 0.0000 -0.0004 -0.0376 0.248 + 104 -2.9762 3.0955 1.1548 -0.5659 -0.0089 -0.2345 -0.1829 -0.0001 0.0000 -0.0006 -0.0377 0.247 + 105 -3.3476 2.9485 1.1122 -0.5412 -0.0091 -0.2355 -0.1837 -0.0002 0.0000 -0.0007 -0.0377 0.246 + 106 -3.7210 2.8008 1.0564 -0.5145 -0.0096 -0.2357 -0.1838 -0.0002 0.0000 -0.0009 -0.0376 0.245 + 107 -4.0924 2.6538 0.9900 -0.4861 -0.0102 -0.2350 -0.1833 -0.0002 0.0000 -0.0010 -0.0374 0.245 + 108 -4.4577 2.5093 0.9155 -0.4565 -0.0110 -0.2334 -0.1820 -0.0002 0.0000 -0.0012 -0.0370 0.244 + 109 -4.8128 2.3687 0.8353 -0.4264 -0.0119 -0.2310 -0.1801 -0.0002 0.0000 -0.0014 -0.0364 0.242 + 110 -5.1540 2.2338 0.7518 -0.3960 -0.0129 -0.2275 -0.1774 -0.0002 0.0000 -0.0017 -0.0356 0.240 + 111 -5.4774 2.1058 0.6671 -0.3654 -0.0141 -0.2226 -0.1736 -0.0002 0.0000 -0.0022 -0.0344 0.238 + 112 -5.7795 1.9862 0.5830 -0.3346 -0.0155 -0.2162 -0.1686 -0.0002 0.0000 -0.0028 -0.0328 0.233 + 113 -6.0570 1.8764 0.5012 -0.3033 -0.0171 -0.2074 -0.1617 -0.0002 0.0000 -0.0037 -0.0307 0.227 + 114 -6.3069 1.7776 0.4225 -0.2712 -0.0187 -0.1958 -0.1527 -0.0002 0.0000 -0.0047 -0.0279 0.219 + 115 -6.5264 1.6907 0.3478 -0.2380 -0.0204 -0.1806 -0.1409 -0.0003 0.0000 -0.0059 -0.0244 0.208 + 116 -6.7314 1.6096 0.3326 -0.2015 -0.0221 -0.1606 -0.1253 -0.0003 0.0000 -0.0070 -0.0202 0.194 + 117 -6.9144 1.5372 0.2507 -0.1602 -0.0237 -0.1337 -0.1043 -0.0004 0.0000 -0.0077 -0.0152 0.176 + 118 -7.0535 1.4822 0.1746 -0.1163 -0.0249 -0.1007 -0.0785 -0.0005 0.0000 -0.0074 -0.0101 0.156 + 119 -7.1471 1.4451 0.1029 -0.0706 -0.0258 -0.0627 -0.0489 -0.0005 0.0000 -0.0055 -0.0056 0.138 + 120 -7.1941 1.4265 0.0340 -0.0237 -0.0263 -0.0213 -0.0166 -0.0005 0.0000 -0.0020 -0.0017 0.128 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = -0.00000 CYsurf = -0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = 0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.800 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.780 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.766 - 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.749 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.721 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.689 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.651 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.600 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.542 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.475 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.419 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.392 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.368 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.349 + 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.786 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.771 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.769 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.750 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.727 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.698 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.661 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.607 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.547 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.474 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.429 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.397 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.369 + 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.354 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.330 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.320 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.304 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.295 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.286 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.280 - 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.274 - 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.262 - 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.254 - 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.243 - 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.225 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.217 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.200 - 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.177 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.166 - 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.158 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.312 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.300 + 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.288 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.284 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.273 + 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.268 + 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.260 + 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.255 + 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.245 + 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.233 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.213 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.198 + 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.175 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.153 + 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.146 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00972 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.02397 - CDsurf = 0.00022 Cnsurf = 0.00000 + CLsurf = -0.00979 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.02390 + CDsurf = 0.00022 Cnsurf = -0.00000 CDisurf = 0.00022 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00980 CDsurf = 0.00022 + CLsurf = -0.00987 CDsurf = 0.00022 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.2423 -0.0593 -0.1133 -0.0091 0.0001 0.0000 -0.0004 0.0003 0.209 - 152 -1.3090 31.2096 11.6724 -0.3263 -0.0548 -0.0406 -0.0105 0.0002 0.0000 -0.0008 0.0004 0.172 - 153 -0.9350 34.0626 12.7394 -0.3473 -0.0333 -0.0249 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.094 - 154 -0.5610 36.1619 13.5246 -0.3526 -0.0219 -0.0164 -0.0097 0.0003 0.0000 -0.0021 0.0002 0.038 - 155 -0.1870 37.5332 14.0374 -0.3540 -0.0173 -0.0109 -0.0094 0.0003 0.0000 -0.0023 0.0001 0.010 - 156 0.1870 37.5332 14.0374 -0.3540 -0.0173 -0.0109 -0.0094 0.0003 0.0000 -0.0023 0.0001 0.010 - 157 0.5610 36.1619 13.5246 -0.3526 -0.0219 -0.0164 -0.0097 0.0003 0.0000 -0.0021 0.0002 0.038 - 158 0.9350 34.0626 12.7394 -0.3473 -0.0333 -0.0249 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.094 - 159 1.3090 31.2096 11.6724 -0.3263 -0.0548 -0.0406 -0.0105 0.0002 0.0000 -0.0008 0.0004 0.172 - 160 1.6830 26.5957 9.9468 -0.2423 -0.0593 -0.1133 -0.0091 0.0001 0.0000 -0.0004 0.0003 0.209 + 151 -1.6830 26.5957 9.9468 -0.2440 -0.0594 -0.1141 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.212 + 152 -1.3090 31.2096 11.6724 -0.3286 -0.0548 -0.0409 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.174 + 153 -0.9350 34.0626 12.7394 -0.3497 -0.0331 -0.0250 -0.0103 0.0002 0.0000 -0.0016 0.0003 0.097 + 154 -0.5610 36.1619 13.5246 -0.3551 -0.0217 -0.0165 -0.0098 0.0003 0.0000 -0.0021 0.0002 0.041 + 155 -0.1870 37.5332 14.0374 -0.3564 -0.0171 -0.0110 -0.0095 0.0003 0.0000 -0.0023 0.0001 0.013 + 156 0.1870 37.5332 14.0374 -0.3564 -0.0171 -0.0110 -0.0095 0.0003 0.0000 -0.0023 0.0001 0.013 + 157 0.5610 36.1619 13.5246 -0.3551 -0.0217 -0.0165 -0.0098 0.0003 0.0000 -0.0021 0.0002 0.041 + 158 0.9350 34.0626 12.7394 -0.3497 -0.0331 -0.0250 -0.0103 0.0002 0.0000 -0.0016 0.0003 0.097 + 159 1.3090 31.2096 11.6724 -0.3286 -0.0548 -0.0409 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.174 + 160 1.6830 26.5957 9.9468 -0.2440 -0.0594 -0.1141 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.212 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.877 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.846 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.838 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.030 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.867 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.846 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.830 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.821 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.793 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.766 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.704 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.567 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.288 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.820 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.797 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.771 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.734 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.533 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_01_02.txt b/regression/scripts/AVL/avl_files/strip_forces_case_01_02.txt index 79db56f40a..44b65be229 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_01_02.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_01_02.txt @@ -7,258 +7,258 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09001 Clsurf = -0.01429 - CYsurf = -0.00610 Cmsurf = -0.07162 - CDsurf = 0.00121 Cnsurf = 0.00067 - CDisurf = 0.00121 CDvsurf = 0.00000 + CLsurf = 0.09061 Clsurf = -0.01435 + CYsurf = -0.00610 Cmsurf = -0.07195 + CDsurf = 0.00118 Cnsurf = 0.00067 + CDisurf = 0.00118 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.17609 CDsurf = 0.00237 + CLsurf = 0.17727 CDsurf = 0.00230 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 1.5821 0.0482 0.2631 0.2041 0.0724 0.0000 -0.0102 -0.0499 0.300 - 2 0.1025 7.6885 1.0492 1.5345 0.0475 0.2573 0.1996 0.0163 0.0000 -0.0102 -0.0490 0.301 - 3 0.2837 7.5620 1.7073 1.5269 0.0459 0.2603 0.2019 0.0126 0.0000 -0.0095 -0.0489 0.297 - 4 0.5530 7.3741 2.3052 1.5148 0.0433 0.2648 0.2054 0.0111 0.0000 -0.0084 -0.0487 0.291 - 5 0.9075 7.1267 2.8223 1.4908 0.0402 0.2697 0.2092 0.0095 0.0000 -0.0074 -0.0486 0.285 - 6 1.3432 6.8226 3.2414 1.4505 0.0380 0.2741 0.2126 0.0079 0.0000 -0.0066 -0.0487 0.281 - 7 1.8554 6.4651 3.5491 1.3910 0.0399 0.2774 0.2152 0.0067 0.0000 -0.0063 -0.0490 0.279 - 8 2.4386 6.0582 3.7368 1.3060 0.0400 0.2779 0.2156 0.0046 0.0000 -0.0066 -0.0493 0.281 - 9 3.0862 5.6062 3.8005 1.1985 0.0312 0.2756 0.2138 0.0028 0.0000 -0.0077 -0.0498 0.286 - 10 3.7613 5.1351 3.4440 1.0770 0.0209 0.2704 0.2097 0.0008 0.0000 -0.0096 -0.0506 0.296 - 11 4.4532 4.6522 3.3149 0.9499 0.0112 0.2633 0.2042 -0.0006 0.0000 -0.0126 -0.0519 0.312 - 12 5.1831 4.1429 3.0930 0.8148 -0.0016 0.2536 0.1967 -0.0023 0.0000 -0.0167 -0.0537 0.335 - 13 6.0123 3.7903 3.4706 0.6945 -0.0086 0.2231 0.1832 -0.0027 0.0000 -0.0197 -0.0582 0.357 - 14 6.9353 3.6075 3.3775 0.6085 -0.0058 0.2054 0.1687 -0.0019 0.0000 -0.0202 -0.0555 0.370 - 15 7.8737 3.4215 3.2389 0.5402 -0.0038 0.1923 0.1579 -0.0015 0.0000 -0.0203 -0.0532 0.379 - 16 8.8172 3.2345 3.0619 0.4840 -0.0024 0.1822 0.1496 -0.0012 0.0000 -0.0203 -0.0513 0.386 - 17 9.7556 3.0486 2.8543 0.4364 -0.0016 0.1743 0.1431 -0.0010 0.0000 -0.0202 -0.0498 0.391 - 18 10.6786 2.8657 2.6240 0.3953 -0.0010 0.1680 0.1379 -0.0009 0.0000 -0.0202 -0.0486 0.396 - 19 11.5760 2.6879 2.3787 0.3592 -0.0005 0.1628 0.1336 -0.0007 0.0000 -0.0201 -0.0476 0.400 - 20 12.4328 2.5181 2.1010 0.3272 0.0000 0.1583 0.1299 -0.0007 0.0000 -0.0200 -0.0466 0.404 - 21 13.2400 2.3582 1.8520 0.2984 0.0007 0.1541 0.1265 -0.0006 0.0000 -0.0199 -0.0458 0.407 - 22 13.9941 2.2087 1.6074 0.2717 0.0015 0.1498 0.1230 -0.0005 0.0000 -0.0197 -0.0448 0.410 - 23 14.6868 2.0715 1.3716 0.2464 0.0027 0.1448 0.1189 -0.0005 0.0000 -0.0194 -0.0436 0.413 - 24 15.3105 1.9479 1.1479 0.2212 0.0042 0.1383 0.1135 -0.0004 0.0000 -0.0188 -0.0420 0.416 - 25 15.8583 1.8393 0.9381 0.1947 0.0062 0.1289 0.1059 -0.0003 0.0000 -0.0180 -0.0396 0.420 - 26 16.3244 1.7470 0.7427 0.1653 0.0085 0.1153 0.0946 -0.0002 0.0000 -0.0170 -0.0361 0.430 - 27 16.6722 1.4928 0.4131 0.1336 0.0111 0.2988 0.0895 -0.0004 0.0000 -0.0144 -0.0172 0.411 - 28 16.9098 1.1466 0.2292 0.1010 0.0155 0.2941 0.0881 -0.0009 0.0000 -0.0102 -0.0151 0.366 - 29 17.0696 0.9138 0.1104 0.0637 0.0198 0.2328 0.0698 -0.0012 0.0000 -0.0044 -0.0102 0.314 - 30 17.1499 0.7967 0.0322 0.0218 0.0222 0.0915 0.0274 -0.0010 0.0000 -0.0007 -0.0035 0.275 + 1 0.0114 7.7520 0.3539 1.5980 0.0482 0.2658 0.2061 0.0724 0.0000 -0.0116 -0.0514 0.306 + 2 0.1025 7.6885 1.0491 1.5497 0.0476 0.2599 0.2016 0.0163 0.0000 -0.0115 -0.0504 0.307 + 3 0.2837 7.5620 1.7073 1.5424 0.0462 0.2630 0.2040 0.0126 0.0000 -0.0108 -0.0503 0.303 + 4 0.5530 7.3741 2.3052 1.5301 0.0439 0.2675 0.2075 0.0108 0.0000 -0.0097 -0.0502 0.297 + 5 0.9075 7.1267 2.8223 1.5065 0.0408 0.2725 0.2114 0.0097 0.0000 -0.0087 -0.0501 0.291 + 6 1.3432 6.8226 3.2414 1.4658 0.0386 0.2770 0.2148 0.0078 0.0000 -0.0079 -0.0502 0.287 + 7 1.8554 6.4651 3.5491 1.4040 0.0405 0.2800 0.2172 0.0055 0.0000 -0.0075 -0.0503 0.284 + 8 2.4386 6.0582 3.7368 1.3192 0.0406 0.2807 0.2178 0.0043 0.0000 -0.0076 -0.0506 0.285 + 9 3.0862 5.6062 3.8005 1.2112 0.0320 0.2785 0.2160 0.0027 0.0000 -0.0085 -0.0510 0.289 + 10 3.7613 5.1351 3.4440 1.0877 0.0215 0.2731 0.2118 0.0015 0.0000 -0.0101 -0.0514 0.298 + 11 4.4532 4.6522 3.3149 0.9576 0.0111 0.2654 0.2058 -0.0006 0.0000 -0.0125 -0.0521 0.311 + 12 5.1831 4.1429 3.0930 0.8190 -0.0022 0.2549 0.1977 -0.0023 0.0000 -0.0158 -0.0531 0.330 + 13 6.0123 3.7903 3.4706 0.6969 -0.0091 0.2239 0.1839 -0.0027 0.0000 -0.0183 -0.0571 0.349 + 14 6.9353 3.6075 3.3775 0.6105 -0.0060 0.2061 0.1692 -0.0019 0.0000 -0.0187 -0.0542 0.361 + 15 7.8737 3.4215 3.2389 0.5420 -0.0039 0.1929 0.1584 -0.0015 0.0000 -0.0188 -0.0519 0.369 + 16 8.8172 3.2345 3.0619 0.4855 -0.0025 0.1828 0.1501 -0.0012 0.0000 -0.0187 -0.0500 0.375 + 17 9.7556 3.0486 2.8543 0.4376 -0.0016 0.1748 0.1435 -0.0010 0.0000 -0.0187 -0.0485 0.380 + 18 10.6786 2.8657 2.6239 0.3963 -0.0010 0.1684 0.1383 -0.0009 0.0000 -0.0186 -0.0472 0.384 + 19 11.5760 2.6879 2.3787 0.3601 -0.0005 0.1632 0.1340 -0.0008 0.0000 -0.0185 -0.0462 0.388 + 20 12.4328 2.5181 2.1010 0.3280 0.0000 0.1586 0.1302 -0.0007 0.0000 -0.0184 -0.0453 0.391 + 21 13.2400 2.3582 1.8520 0.2990 0.0007 0.1544 0.1268 -0.0006 0.0000 -0.0183 -0.0444 0.394 + 22 13.9941 2.2087 1.6074 0.2722 0.0015 0.1501 0.1232 -0.0005 0.0000 -0.0181 -0.0434 0.397 + 23 14.6868 2.0715 1.3716 0.2467 0.0027 0.1450 0.1191 -0.0005 0.0000 -0.0178 -0.0422 0.399 + 24 15.3105 1.9479 1.1479 0.2213 0.0042 0.1384 0.1136 -0.0004 0.0000 -0.0172 -0.0406 0.402 + 25 15.8583 1.8393 0.9381 0.1946 0.0061 0.1289 0.1058 -0.0003 0.0000 -0.0164 -0.0381 0.405 + 26 16.3244 1.7470 0.7427 0.1649 0.0082 0.1150 0.0944 -0.0002 0.0000 -0.0154 -0.0347 0.414 + 27 16.6722 1.4928 0.4131 0.1332 0.0108 0.2979 0.0892 -0.0005 0.0000 -0.0131 -0.0166 0.397 + 28 16.9098 1.1466 0.2292 0.1009 0.0155 0.2937 0.0880 -0.0009 0.0000 -0.0092 -0.0146 0.354 + 29 17.0696 0.9138 0.1104 0.0638 0.0200 0.2329 0.0698 -0.0012 0.0000 -0.0038 -0.0099 0.305 + 30 17.1499 0.7967 0.0322 0.0219 0.0229 0.0918 0.0275 -0.0010 0.0000 -0.0005 -0.0035 0.269 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09000 Clsurf = 0.01429 - CYsurf = 0.00610 Cmsurf = -0.07162 - CDsurf = 0.00121 Cnsurf = -0.00067 - CDisurf = 0.00121 CDvsurf = 0.00000 + CLsurf = 0.09061 Clsurf = 0.01435 + CYsurf = 0.00610 Cmsurf = -0.07195 + CDsurf = 0.00118 Cnsurf = -0.00067 + CDisurf = 0.00118 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.17608 CDsurf = 0.00237 + CLsurf = 0.17727 CDsurf = 0.00230 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 1.5821 0.0482 0.2631 0.2041 0.0724 0.0000 -0.0102 0.0499 0.300 - 32 -0.1025 7.6885 1.0492 1.5345 0.0475 0.2573 0.1996 0.0163 0.0000 -0.0102 0.0490 0.301 - 33 -0.2837 7.5620 1.7073 1.5269 0.0459 0.2603 0.2019 0.0126 0.0000 -0.0095 0.0489 0.297 - 34 -0.5530 7.3741 2.3052 1.5148 0.0433 0.2648 0.2054 0.0111 0.0000 -0.0084 0.0487 0.291 - 35 -0.9075 7.1267 2.8223 1.4907 0.0402 0.2697 0.2092 0.0095 0.0000 -0.0074 0.0486 0.285 - 36 -1.3432 6.8226 3.2414 1.4505 0.0380 0.2741 0.2126 0.0079 0.0000 -0.0066 0.0487 0.281 - 37 -1.8554 6.4651 3.5491 1.3910 0.0399 0.2774 0.2152 0.0067 0.0000 -0.0063 0.0490 0.279 - 38 -2.4386 6.0582 3.7368 1.3059 0.0400 0.2779 0.2156 0.0046 0.0000 -0.0066 0.0493 0.281 - 39 -3.0862 5.6062 3.8005 1.1985 0.0312 0.2756 0.2138 0.0028 0.0000 -0.0077 0.0498 0.286 - 40 -3.7613 5.1351 3.4440 1.0770 0.0209 0.2704 0.2097 0.0008 0.0000 -0.0096 0.0506 0.296 - 41 -4.4532 4.6522 3.3149 0.9498 0.0112 0.2633 0.2042 -0.0006 0.0000 -0.0126 0.0519 0.312 - 42 -5.1831 4.1429 3.0930 0.8148 -0.0016 0.2536 0.1967 -0.0023 0.0000 -0.0167 0.0537 0.335 - 43 -6.0123 3.7903 3.4706 0.6945 -0.0086 0.2231 0.1832 -0.0027 0.0000 -0.0197 0.0582 0.357 - 44 -6.9353 3.6075 3.3775 0.6085 -0.0058 0.2054 0.1687 -0.0019 0.0000 -0.0202 0.0555 0.370 - 45 -7.8737 3.4215 3.2389 0.5402 -0.0038 0.1923 0.1579 -0.0015 0.0000 -0.0203 0.0532 0.379 - 46 -8.8172 3.2345 3.0619 0.4840 -0.0024 0.1822 0.1496 -0.0012 0.0000 -0.0203 0.0513 0.386 - 47 -9.7556 3.0486 2.8543 0.4364 -0.0016 0.1743 0.1431 -0.0010 0.0000 -0.0202 0.0498 0.391 - 48 -10.6786 2.8657 2.6240 0.3953 -0.0010 0.1680 0.1379 -0.0009 0.0000 -0.0202 0.0486 0.396 - 49 -11.5760 2.6879 2.3787 0.3592 -0.0005 0.1627 0.1336 -0.0007 0.0000 -0.0201 0.0476 0.400 - 50 -12.4328 2.5181 2.1010 0.3272 0.0000 0.1583 0.1299 -0.0007 0.0000 -0.0200 0.0466 0.404 - 51 -13.2400 2.3582 1.8520 0.2984 0.0007 0.1541 0.1265 -0.0006 0.0000 -0.0199 0.0458 0.407 - 52 -13.9941 2.2087 1.6074 0.2717 0.0015 0.1498 0.1230 -0.0005 0.0000 -0.0197 0.0448 0.410 - 53 -14.6868 2.0715 1.3716 0.2464 0.0027 0.1448 0.1189 -0.0005 0.0000 -0.0194 0.0436 0.413 - 54 -15.3105 1.9479 1.1479 0.2212 0.0042 0.1383 0.1135 -0.0004 0.0000 -0.0188 0.0420 0.416 - 55 -15.8583 1.8393 0.9381 0.1947 0.0062 0.1289 0.1059 -0.0003 0.0000 -0.0180 0.0396 0.420 - 56 -16.3244 1.7470 0.7427 0.1653 0.0085 0.1153 0.0946 -0.0002 0.0000 -0.0170 0.0361 0.430 - 57 -16.6722 1.4928 0.4131 0.1336 0.0111 0.2988 0.0895 -0.0004 0.0000 -0.0144 0.0172 0.411 - 58 -16.9098 1.1466 0.2292 0.1010 0.0155 0.2941 0.0881 -0.0009 0.0000 -0.0102 0.0151 0.366 - 59 -17.0696 0.9138 0.1104 0.0637 0.0198 0.2328 0.0698 -0.0012 0.0000 -0.0044 0.0102 0.314 - 60 -17.1499 0.7967 0.0322 0.0218 0.0222 0.0915 0.0274 -0.0010 0.0000 -0.0007 0.0035 0.275 + 31 -0.0114 7.7520 0.3539 1.5980 0.0482 0.2658 0.2061 0.0724 0.0000 -0.0116 0.0514 0.306 + 32 -0.1025 7.6885 1.0491 1.5497 0.0476 0.2599 0.2016 0.0163 0.0000 -0.0115 0.0504 0.307 + 33 -0.2837 7.5620 1.7073 1.5424 0.0462 0.2630 0.2040 0.0126 0.0000 -0.0108 0.0503 0.303 + 34 -0.5530 7.3741 2.3052 1.5301 0.0439 0.2675 0.2075 0.0108 0.0000 -0.0097 0.0502 0.297 + 35 -0.9075 7.1267 2.8223 1.5065 0.0408 0.2725 0.2114 0.0097 0.0000 -0.0087 0.0501 0.291 + 36 -1.3432 6.8226 3.2414 1.4658 0.0386 0.2770 0.2148 0.0078 0.0000 -0.0079 0.0502 0.287 + 37 -1.8554 6.4651 3.5491 1.4040 0.0405 0.2800 0.2172 0.0055 0.0000 -0.0075 0.0503 0.284 + 38 -2.4386 6.0582 3.7368 1.3192 0.0406 0.2807 0.2178 0.0043 0.0000 -0.0076 0.0506 0.285 + 39 -3.0862 5.6062 3.8005 1.2112 0.0320 0.2785 0.2160 0.0027 0.0000 -0.0085 0.0510 0.289 + 40 -3.7613 5.1351 3.4440 1.0877 0.0215 0.2731 0.2118 0.0015 0.0000 -0.0101 0.0514 0.298 + 41 -4.4532 4.6522 3.3149 0.9576 0.0111 0.2654 0.2058 -0.0006 0.0000 -0.0125 0.0521 0.311 + 42 -5.1831 4.1429 3.0930 0.8190 -0.0022 0.2549 0.1977 -0.0023 0.0000 -0.0158 0.0531 0.330 + 43 -6.0123 3.7903 3.4706 0.6969 -0.0091 0.2239 0.1839 -0.0027 0.0000 -0.0183 0.0571 0.349 + 44 -6.9353 3.6075 3.3775 0.6105 -0.0060 0.2061 0.1692 -0.0019 0.0000 -0.0187 0.0542 0.361 + 45 -7.8737 3.4215 3.2389 0.5420 -0.0039 0.1929 0.1584 -0.0015 0.0000 -0.0188 0.0519 0.369 + 46 -8.8172 3.2345 3.0619 0.4855 -0.0025 0.1828 0.1501 -0.0012 0.0000 -0.0187 0.0500 0.375 + 47 -9.7556 3.0486 2.8543 0.4376 -0.0016 0.1748 0.1435 -0.0010 0.0000 -0.0187 0.0485 0.380 + 48 -10.6786 2.8657 2.6239 0.3963 -0.0010 0.1684 0.1383 -0.0009 0.0000 -0.0186 0.0472 0.384 + 49 -11.5760 2.6879 2.3787 0.3601 -0.0005 0.1632 0.1340 -0.0008 0.0000 -0.0185 0.0462 0.388 + 50 -12.4328 2.5181 2.1010 0.3280 0.0000 0.1586 0.1302 -0.0007 0.0000 -0.0184 0.0453 0.391 + 51 -13.2400 2.3582 1.8520 0.2990 0.0007 0.1544 0.1268 -0.0006 0.0000 -0.0183 0.0444 0.394 + 52 -13.9941 2.2087 1.6074 0.2722 0.0015 0.1501 0.1232 -0.0005 0.0000 -0.0181 0.0434 0.397 + 53 -14.6868 2.0715 1.3716 0.2467 0.0027 0.1450 0.1191 -0.0005 0.0000 -0.0178 0.0422 0.399 + 54 -15.3105 1.9479 1.1479 0.2213 0.0042 0.1384 0.1136 -0.0004 0.0000 -0.0172 0.0406 0.402 + 55 -15.8583 1.8393 0.9381 0.1946 0.0061 0.1289 0.1058 -0.0003 0.0000 -0.0164 0.0381 0.405 + 56 -16.3244 1.7470 0.7427 0.1649 0.0082 0.1150 0.0944 -0.0002 0.0000 -0.0154 0.0347 0.414 + 57 -16.6722 1.4928 0.4131 0.1332 0.0108 0.2979 0.0892 -0.0005 0.0000 -0.0131 0.0166 0.397 + 58 -16.9098 1.1466 0.2292 0.1009 0.0155 0.2937 0.0880 -0.0009 0.0000 -0.0092 0.0146 0.354 + 59 -17.0696 0.9138 0.1104 0.0638 0.0200 0.2329 0.0698 -0.0012 0.0000 -0.0038 0.0099 0.305 + 60 -17.1499 0.7967 0.0322 0.0219 0.0229 0.0918 0.0275 -0.0010 0.0000 -0.0005 0.0035 0.269 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01236 Clsurf = 0.00112 - CYsurf = 0.00199 Cmsurf = 0.05902 - CDsurf = -0.00017 Cnsurf = -0.00119 - CDisurf = -0.00017 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01249 Clsurf = 0.00113 + CYsurf = 0.00201 Cmsurf = 0.05965 + CDsurf = -0.00018 Cnsurf = -0.00120 + CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.07533 CDsurf = -0.00105 + CLsurf = -0.07614 CDsurf = -0.00108 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.3048 0.0109 -0.0920 -0.0714 0.0119 0.0000 0.0033 0.0178 0.296 - 62 0.0418 4.2566 0.2392 -0.3231 0.0106 -0.0979 -0.0759 0.0002 0.0000 0.0031 0.0186 0.291 - 63 0.1156 4.2274 0.3930 -0.3245 0.0103 -0.0990 -0.0768 -0.0005 0.0000 0.0028 0.0186 0.287 - 64 0.2254 4.1839 0.5386 -0.3248 0.0100 -0.1001 -0.0776 -0.0007 0.0000 0.0024 0.0184 0.281 - 65 0.3698 4.1268 0.6730 -0.3246 0.0098 -0.1014 -0.0786 -0.0009 0.0000 0.0019 0.0182 0.274 - 66 0.5474 4.0565 0.7936 -0.3238 0.0095 -0.1030 -0.0798 -0.0010 0.0000 0.0014 0.0180 0.267 - 67 0.7617 3.9717 0.9441 -0.3220 0.0094 -0.1046 -0.0811 -0.0011 0.0000 0.0009 0.0178 0.261 - 68 1.0116 3.8728 1.0344 -0.3190 0.0095 -0.1062 -0.0824 -0.0012 0.0000 0.0004 0.0177 0.255 - 69 1.2891 3.7630 1.1046 -0.3145 0.0098 -0.1078 -0.0836 -0.0013 0.0000 0.0000 0.0176 0.250 - 70 1.5912 3.6435 1.1542 -0.3079 0.0103 -0.1090 -0.0845 -0.0014 0.0000 -0.0003 0.0176 0.246 - 71 1.9146 3.5155 1.1831 -0.2991 0.0108 -0.1097 -0.0851 -0.0014 0.0000 -0.0006 0.0175 0.244 - 72 2.2558 3.3805 1.1921 -0.2882 0.0110 -0.1100 -0.0852 -0.0015 0.0000 -0.0007 0.0174 0.241 - 73 2.6109 3.2400 1.1821 -0.2750 0.0109 -0.1095 -0.0849 -0.0015 0.0000 -0.0008 0.0172 0.240 - 74 2.9762 3.0955 1.1548 -0.2597 0.0104 -0.1082 -0.0839 -0.0014 0.0000 -0.0009 0.0169 0.239 - 75 3.3476 2.9485 1.1122 -0.2428 0.0098 -0.1062 -0.0823 -0.0014 0.0000 -0.0009 0.0166 0.239 - 76 3.7210 2.8008 1.0564 -0.2246 0.0090 -0.1035 -0.0802 -0.0013 0.0000 -0.0009 0.0162 0.239 - 77 4.0924 2.6538 0.9900 -0.2059 0.0083 -0.1001 -0.0776 -0.0012 0.0000 -0.0009 0.0156 0.239 - 78 4.4577 2.5093 0.9155 -0.1870 0.0076 -0.0961 -0.0745 -0.0011 0.0000 -0.0009 0.0150 0.238 - 79 4.8128 2.3687 0.8353 -0.1685 0.0069 -0.0917 -0.0711 -0.0010 0.0000 -0.0008 0.0143 0.238 - 80 5.1540 2.2338 0.7518 -0.1507 0.0063 -0.0870 -0.0674 -0.0009 0.0000 -0.0009 0.0135 0.237 - 81 5.4774 2.1058 0.6671 -0.1338 0.0057 -0.0819 -0.0635 -0.0008 0.0000 -0.0009 0.0126 0.235 - 82 5.7795 1.9862 0.5830 -0.1180 0.0051 -0.0766 -0.0594 -0.0007 0.0000 -0.0010 0.0116 0.232 - 83 6.0570 1.8764 0.5012 -0.1031 0.0045 -0.0709 -0.0550 -0.0007 0.0000 -0.0012 0.0106 0.228 - 84 6.3069 1.7776 0.4225 -0.0893 0.0039 -0.0648 -0.0502 -0.0006 0.0000 -0.0015 0.0094 0.221 - 85 6.5264 1.6907 0.3478 -0.0760 0.0033 -0.0580 -0.0450 -0.0005 0.0000 -0.0017 0.0080 0.211 - 86 6.7314 1.6096 0.3326 -0.0626 0.0027 -0.0502 -0.0389 -0.0004 0.0000 -0.0020 0.0065 0.199 - 87 6.9144 1.5372 0.2507 -0.0486 0.0022 -0.0408 -0.0316 -0.0003 0.0000 -0.0022 0.0049 0.182 - 88 7.0535 1.4822 0.1746 -0.0347 0.0018 -0.0302 -0.0234 -0.0003 0.0000 -0.0020 0.0032 0.163 - 89 7.1471 1.4451 0.1029 -0.0208 0.0015 -0.0186 -0.0144 -0.0002 0.0000 -0.0015 0.0018 0.147 - 90 7.1941 1.4265 0.0340 -0.0069 0.0014 -0.0063 -0.0049 -0.0001 0.0000 -0.0005 0.0006 0.137 + 61 0.0047 4.2713 0.0803 -0.3082 0.0110 -0.0931 -0.0722 0.0122 0.0000 0.0033 0.0180 0.296 + 62 0.0418 4.2566 0.2392 -0.3270 0.0107 -0.0991 -0.0768 0.0003 0.0000 0.0031 0.0188 0.291 + 63 0.1156 4.2274 0.3930 -0.3284 0.0104 -0.1002 -0.0777 -0.0005 0.0000 0.0029 0.0188 0.287 + 64 0.2254 4.1839 0.5386 -0.3287 0.0101 -0.1013 -0.0786 -0.0008 0.0000 0.0024 0.0186 0.281 + 65 0.3698 4.1268 0.6730 -0.3285 0.0099 -0.1027 -0.0796 -0.0009 0.0000 0.0019 0.0184 0.274 + 66 0.5474 4.0565 0.7936 -0.3277 0.0096 -0.1042 -0.0808 -0.0010 0.0000 0.0014 0.0182 0.267 + 67 0.7617 3.9717 0.9441 -0.3259 0.0095 -0.1058 -0.0821 -0.0011 0.0000 0.0009 0.0180 0.261 + 68 1.0116 3.8728 1.0344 -0.3229 0.0096 -0.1076 -0.0834 -0.0013 0.0000 0.0004 0.0179 0.255 + 69 1.2891 3.7630 1.1046 -0.3182 0.0099 -0.1091 -0.0846 -0.0014 0.0000 0.0000 0.0178 0.250 + 70 1.5912 3.6435 1.1542 -0.3115 0.0104 -0.1103 -0.0855 -0.0014 0.0000 -0.0003 0.0178 0.246 + 71 1.9146 3.5155 1.1831 -0.3027 0.0109 -0.1111 -0.0861 -0.0015 0.0000 -0.0006 0.0177 0.243 + 72 2.2558 3.3805 1.1921 -0.2916 0.0112 -0.1113 -0.0863 -0.0015 0.0000 -0.0007 0.0176 0.241 + 73 2.6109 3.2400 1.1821 -0.2781 0.0110 -0.1107 -0.0858 -0.0015 0.0000 -0.0009 0.0174 0.240 + 74 2.9762 3.0955 1.1548 -0.2626 0.0105 -0.1094 -0.0848 -0.0015 0.0000 -0.0009 0.0171 0.239 + 75 3.3476 2.9485 1.1122 -0.2454 0.0099 -0.1074 -0.0832 -0.0014 0.0000 -0.0009 0.0168 0.239 + 76 3.7210 2.8008 1.0564 -0.2270 0.0091 -0.1046 -0.0811 -0.0013 0.0000 -0.0009 0.0163 0.239 + 77 4.0924 2.6538 0.9900 -0.2080 0.0084 -0.1011 -0.0784 -0.0012 0.0000 -0.0009 0.0158 0.239 + 78 4.4577 2.5093 0.9155 -0.1888 0.0076 -0.0970 -0.0752 -0.0011 0.0000 -0.0009 0.0151 0.238 + 79 4.8128 2.3687 0.8353 -0.1700 0.0070 -0.0926 -0.0718 -0.0010 0.0000 -0.0009 0.0144 0.238 + 80 5.1540 2.2338 0.7518 -0.1519 0.0063 -0.0877 -0.0680 -0.0009 0.0000 -0.0009 0.0136 0.237 + 81 5.4774 2.1058 0.6671 -0.1348 0.0057 -0.0826 -0.0640 -0.0008 0.0000 -0.0009 0.0127 0.235 + 82 5.7795 1.9862 0.5830 -0.1188 0.0051 -0.0772 -0.0598 -0.0008 0.0000 -0.0011 0.0117 0.232 + 83 6.0570 1.8764 0.5012 -0.1039 0.0045 -0.0714 -0.0554 -0.0007 0.0000 -0.0012 0.0106 0.228 + 84 6.3069 1.7776 0.4225 -0.0898 0.0039 -0.0652 -0.0505 -0.0006 0.0000 -0.0015 0.0094 0.221 + 85 6.5264 1.6907 0.3478 -0.0765 0.0033 -0.0583 -0.0452 -0.0005 0.0000 -0.0017 0.0081 0.212 + 86 6.7314 1.6096 0.3326 -0.0630 0.0027 -0.0505 -0.0391 -0.0004 0.0000 -0.0020 0.0066 0.199 + 87 6.9144 1.5372 0.2507 -0.0489 0.0022 -0.0410 -0.0318 -0.0003 0.0000 -0.0022 0.0049 0.182 + 88 7.0535 1.4822 0.1746 -0.0348 0.0018 -0.0303 -0.0235 -0.0003 0.0000 -0.0020 0.0032 0.164 + 89 7.1471 1.4451 0.1029 -0.0209 0.0015 -0.0187 -0.0145 -0.0002 0.0000 -0.0015 0.0018 0.147 + 90 7.1941 1.4265 0.0340 -0.0070 0.0014 -0.0063 -0.0049 -0.0001 0.0000 -0.0006 0.0006 0.137 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01236 Clsurf = -0.00112 - CYsurf = -0.00199 Cmsurf = 0.05902 - CDsurf = -0.00017 Cnsurf = 0.00119 - CDisurf = -0.00017 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01249 Clsurf = -0.00113 + CYsurf = -0.00201 Cmsurf = 0.05965 + CDsurf = -0.00018 Cnsurf = 0.00120 + CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.07533 CDsurf = -0.00105 + CLsurf = -0.07614 CDsurf = -0.00108 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.3048 0.0109 -0.0920 -0.0714 0.0119 0.0000 0.0033 -0.0178 0.296 - 92 -0.0418 4.2566 0.2392 -0.3231 0.0106 -0.0979 -0.0759 0.0002 0.0000 0.0031 -0.0186 0.291 - 93 -0.1156 4.2274 0.3930 -0.3245 0.0103 -0.0990 -0.0768 -0.0005 0.0000 0.0028 -0.0186 0.287 - 94 -0.2254 4.1839 0.5386 -0.3248 0.0100 -0.1001 -0.0776 -0.0007 0.0000 0.0024 -0.0184 0.281 - 95 -0.3698 4.1268 0.6730 -0.3246 0.0098 -0.1014 -0.0786 -0.0009 0.0000 0.0019 -0.0182 0.274 - 96 -0.5474 4.0565 0.7936 -0.3238 0.0095 -0.1030 -0.0798 -0.0010 0.0000 0.0014 -0.0180 0.267 - 97 -0.7617 3.9717 0.9441 -0.3220 0.0094 -0.1046 -0.0811 -0.0011 0.0000 0.0009 -0.0178 0.261 - 98 -1.0116 3.8728 1.0344 -0.3190 0.0095 -0.1062 -0.0824 -0.0012 0.0000 0.0004 -0.0177 0.255 - 99 -1.2891 3.7630 1.1046 -0.3145 0.0098 -0.1078 -0.0836 -0.0013 0.0000 0.0000 -0.0176 0.250 - 100 -1.5912 3.6435 1.1542 -0.3079 0.0103 -0.1090 -0.0845 -0.0014 0.0000 -0.0003 -0.0176 0.246 - 101 -1.9146 3.5155 1.1831 -0.2991 0.0108 -0.1097 -0.0851 -0.0014 0.0000 -0.0006 -0.0175 0.244 - 102 -2.2558 3.3805 1.1921 -0.2882 0.0110 -0.1100 -0.0852 -0.0015 0.0000 -0.0007 -0.0174 0.241 - 103 -2.6109 3.2400 1.1821 -0.2749 0.0109 -0.1095 -0.0849 -0.0015 0.0000 -0.0008 -0.0172 0.240 - 104 -2.9762 3.0955 1.1548 -0.2597 0.0104 -0.1082 -0.0839 -0.0014 0.0000 -0.0009 -0.0169 0.239 - 105 -3.3476 2.9485 1.1122 -0.2428 0.0098 -0.1062 -0.0823 -0.0014 0.0000 -0.0009 -0.0166 0.239 - 106 -3.7210 2.8008 1.0564 -0.2246 0.0090 -0.1035 -0.0802 -0.0013 0.0000 -0.0009 -0.0162 0.239 - 107 -4.0924 2.6538 0.9900 -0.2059 0.0083 -0.1001 -0.0776 -0.0012 0.0000 -0.0009 -0.0156 0.239 - 108 -4.4577 2.5093 0.9155 -0.1870 0.0076 -0.0961 -0.0745 -0.0011 0.0000 -0.0009 -0.0150 0.238 - 109 -4.8128 2.3687 0.8353 -0.1685 0.0069 -0.0917 -0.0711 -0.0010 0.0000 -0.0008 -0.0143 0.238 - 110 -5.1540 2.2338 0.7518 -0.1507 0.0063 -0.0870 -0.0674 -0.0009 0.0000 -0.0009 -0.0135 0.237 - 111 -5.4774 2.1058 0.6671 -0.1338 0.0057 -0.0819 -0.0635 -0.0008 0.0000 -0.0009 -0.0126 0.235 - 112 -5.7795 1.9862 0.5830 -0.1180 0.0051 -0.0766 -0.0594 -0.0007 0.0000 -0.0010 -0.0116 0.232 - 113 -6.0570 1.8764 0.5012 -0.1031 0.0045 -0.0709 -0.0550 -0.0007 0.0000 -0.0012 -0.0106 0.228 - 114 -6.3069 1.7776 0.4225 -0.0893 0.0039 -0.0648 -0.0502 -0.0006 0.0000 -0.0015 -0.0094 0.221 - 115 -6.5264 1.6907 0.3478 -0.0760 0.0033 -0.0580 -0.0450 -0.0005 0.0000 -0.0017 -0.0080 0.211 - 116 -6.7314 1.6096 0.3326 -0.0626 0.0027 -0.0502 -0.0389 -0.0004 0.0000 -0.0020 -0.0065 0.199 - 117 -6.9144 1.5372 0.2507 -0.0486 0.0022 -0.0408 -0.0316 -0.0003 0.0000 -0.0022 -0.0049 0.182 - 118 -7.0535 1.4822 0.1746 -0.0347 0.0018 -0.0302 -0.0234 -0.0003 0.0000 -0.0020 -0.0032 0.163 - 119 -7.1471 1.4451 0.1029 -0.0208 0.0015 -0.0186 -0.0144 -0.0002 0.0000 -0.0015 -0.0018 0.147 - 120 -7.1941 1.4265 0.0340 -0.0069 0.0014 -0.0063 -0.0049 -0.0001 0.0000 -0.0005 -0.0006 0.137 + 91 -0.0047 4.2713 0.0803 -0.3082 0.0110 -0.0931 -0.0722 0.0122 0.0000 0.0033 -0.0180 0.296 + 92 -0.0418 4.2566 0.2392 -0.3270 0.0107 -0.0991 -0.0768 0.0003 0.0000 0.0031 -0.0188 0.291 + 93 -0.1156 4.2274 0.3930 -0.3284 0.0104 -0.1002 -0.0777 -0.0005 0.0000 0.0029 -0.0188 0.287 + 94 -0.2254 4.1839 0.5386 -0.3287 0.0101 -0.1013 -0.0786 -0.0008 0.0000 0.0024 -0.0186 0.281 + 95 -0.3698 4.1268 0.6730 -0.3285 0.0099 -0.1027 -0.0796 -0.0009 0.0000 0.0019 -0.0184 0.274 + 96 -0.5474 4.0565 0.7936 -0.3277 0.0096 -0.1042 -0.0808 -0.0010 0.0000 0.0014 -0.0182 0.267 + 97 -0.7617 3.9717 0.9441 -0.3259 0.0095 -0.1058 -0.0821 -0.0011 0.0000 0.0009 -0.0180 0.261 + 98 -1.0116 3.8728 1.0344 -0.3229 0.0096 -0.1076 -0.0834 -0.0013 0.0000 0.0004 -0.0179 0.255 + 99 -1.2891 3.7630 1.1046 -0.3182 0.0099 -0.1091 -0.0846 -0.0014 0.0000 0.0000 -0.0178 0.250 + 100 -1.5912 3.6435 1.1542 -0.3115 0.0104 -0.1103 -0.0855 -0.0014 0.0000 -0.0003 -0.0178 0.246 + 101 -1.9146 3.5155 1.1831 -0.3027 0.0109 -0.1111 -0.0861 -0.0015 0.0000 -0.0006 -0.0177 0.243 + 102 -2.2558 3.3805 1.1921 -0.2916 0.0112 -0.1113 -0.0863 -0.0015 0.0000 -0.0007 -0.0176 0.241 + 103 -2.6109 3.2400 1.1821 -0.2781 0.0110 -0.1107 -0.0858 -0.0015 0.0000 -0.0009 -0.0174 0.240 + 104 -2.9762 3.0955 1.1548 -0.2626 0.0105 -0.1094 -0.0848 -0.0015 0.0000 -0.0009 -0.0171 0.239 + 105 -3.3476 2.9485 1.1122 -0.2454 0.0099 -0.1074 -0.0832 -0.0014 0.0000 -0.0009 -0.0168 0.239 + 106 -3.7210 2.8008 1.0564 -0.2270 0.0091 -0.1046 -0.0811 -0.0013 0.0000 -0.0009 -0.0163 0.239 + 107 -4.0924 2.6538 0.9900 -0.2080 0.0084 -0.1011 -0.0784 -0.0012 0.0000 -0.0009 -0.0158 0.239 + 108 -4.4577 2.5093 0.9155 -0.1888 0.0076 -0.0970 -0.0752 -0.0011 0.0000 -0.0009 -0.0151 0.238 + 109 -4.8128 2.3687 0.8353 -0.1700 0.0070 -0.0926 -0.0718 -0.0010 0.0000 -0.0009 -0.0144 0.238 + 110 -5.1540 2.2338 0.7518 -0.1519 0.0063 -0.0877 -0.0680 -0.0009 0.0000 -0.0009 -0.0136 0.237 + 111 -5.4774 2.1058 0.6671 -0.1348 0.0057 -0.0826 -0.0640 -0.0008 0.0000 -0.0009 -0.0127 0.235 + 112 -5.7795 1.9862 0.5830 -0.1188 0.0051 -0.0772 -0.0598 -0.0008 0.0000 -0.0011 -0.0117 0.232 + 113 -6.0570 1.8764 0.5012 -0.1039 0.0045 -0.0714 -0.0554 -0.0007 0.0000 -0.0012 -0.0106 0.228 + 114 -6.3069 1.7776 0.4225 -0.0898 0.0039 -0.0652 -0.0505 -0.0006 0.0000 -0.0015 -0.0094 0.221 + 115 -6.5264 1.6907 0.3478 -0.0765 0.0033 -0.0583 -0.0452 -0.0005 0.0000 -0.0017 -0.0081 0.212 + 116 -6.7314 1.6096 0.3326 -0.0630 0.0027 -0.0505 -0.0391 -0.0004 0.0000 -0.0020 -0.0066 0.199 + 117 -6.9144 1.5372 0.2507 -0.0489 0.0022 -0.0410 -0.0318 -0.0003 0.0000 -0.0022 -0.0049 0.182 + 118 -7.0535 1.4822 0.1746 -0.0348 0.0018 -0.0303 -0.0235 -0.0003 0.0000 -0.0020 -0.0032 0.164 + 119 -7.1471 1.4451 0.1029 -0.0209 0.0015 -0.0187 -0.0145 -0.0002 0.0000 -0.0015 -0.0018 0.147 + 120 -7.1941 1.4265 0.0340 -0.0070 0.0014 -0.0063 -0.0049 -0.0001 0.0000 -0.0006 -0.0006 0.137 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.00000 - CDsurf = -0.00000 Cnsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.947 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 125 0.0000 8.6377 2.0517 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 136 0.0000 3.2923 1.3482 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 137 0.0000 3.0597 1.2352 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.770 - 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.376 - 139 0.0000 2.6103 0.9908 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.156 - 140 0.0000 2.3983 0.8670 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.041 - 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.030 - 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.110 - 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.127 - 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.154 - 145 0.0000 1.5493 0.3400 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.175 - 146 0.0000 1.4342 0.2622 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.136 - 147 0.0000 1.3407 0.1933 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.110 - 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.097 - 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.069 - 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.031 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.223 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.225 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.442 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.600 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.849 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 127 0.0000 7.4000 2.2957 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 128 0.0000 6.6646 2.2808 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.789 + 129 0.0000 5.8609 2.1733 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.625 + 130 0.0000 4.9969 1.9773 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.467 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.500 + 132 0.0000 4.2198 1.6478 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.304 + 133 0.0000 3.9932 1.6033 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.169 + 134 0.0000 3.7615 1.5362 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.110 + 135 0.0000 3.5271 1.4499 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.006 + 136 0.0000 3.2923 1.3482 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.083 + 137 0.0000 3.0597 1.2352 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.107 + 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.141 + 139 0.0000 2.6103 0.9908 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.157 + 140 0.0000 2.3983 0.8670 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.192 + 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.197 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.202 + 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.200 + 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.188 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.176 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.167 + 147 0.0000 1.3407 0.1933 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.144 + 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.128 + 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.115 + 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.102 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00507 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.00357 + CLsurf = -0.00514 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00350 CDsurf = 0.00002 Cnsurf = 0.00000 CDisurf = 0.00002 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00511 CDsurf = 0.00002 + CLsurf = -0.00518 CDsurf = 0.00002 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.1324 -0.0064 -0.0628 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.412 - 152 -1.3090 31.2096 11.6724 -0.1729 -0.0000 -0.0216 -0.0055 0.0000 0.0000 0.0007 0.0005 0.374 - 153 -0.9350 34.0626 12.7394 -0.1804 0.0136 -0.0130 -0.0053 0.0000 0.0000 0.0003 0.0006 0.312 - 154 -0.5610 36.1619 13.5246 -0.1805 0.0213 -0.0084 -0.0050 0.0001 0.0000 0.0001 0.0006 0.267 - 155 -0.1870 37.5332 14.0374 -0.1797 0.0249 -0.0056 -0.0048 0.0001 0.0000 -0.0000 0.0008 0.245 - 156 0.1870 37.5332 14.0374 -0.1797 0.0249 -0.0056 -0.0048 0.0001 0.0000 -0.0000 0.0008 0.245 - 157 0.5610 36.1619 13.5246 -0.1805 0.0213 -0.0084 -0.0050 0.0001 0.0000 0.0001 0.0006 0.267 - 158 0.9350 34.0626 12.7394 -0.1804 0.0136 -0.0130 -0.0053 0.0000 0.0000 0.0003 0.0006 0.312 - 159 1.3090 31.2096 11.6724 -0.1729 -0.0000 -0.0216 -0.0055 0.0000 0.0000 0.0007 0.0005 0.374 - 160 1.6830 26.5957 9.9468 -0.1324 -0.0064 -0.0628 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.412 + 151 -1.6830 26.5957 9.9468 -0.1341 -0.0064 -0.0636 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.414 + 152 -1.3090 31.2096 11.6724 -0.1752 0.0000 -0.0219 -0.0056 0.0000 0.0000 0.0007 0.0005 0.377 + 153 -0.9350 34.0626 12.7394 -0.1829 0.0137 -0.0131 -0.0054 0.0000 0.0000 0.0003 0.0006 0.315 + 154 -0.5610 36.1619 13.5246 -0.1830 0.0216 -0.0085 -0.0051 0.0001 0.0000 0.0001 0.0006 0.271 + 155 -0.1870 37.5332 14.0374 -0.1821 0.0251 -0.0056 -0.0049 0.0001 0.0000 -0.0000 0.0008 0.248 + 156 0.1870 37.5332 14.0374 -0.1821 0.0251 -0.0056 -0.0049 0.0001 0.0000 -0.0000 0.0008 0.248 + 157 0.5610 36.1619 13.5246 -0.1830 0.0216 -0.0085 -0.0051 0.0001 0.0000 0.0001 0.0006 0.271 + 158 0.9350 34.0626 12.7394 -0.1829 0.0137 -0.0131 -0.0054 0.0000 0.0000 0.0003 0.0006 0.315 + 159 1.3090 31.2096 11.6724 -0.1752 0.0000 -0.0219 -0.0056 0.0000 0.0000 0.0007 0.0005 0.377 + 160 1.6830 26.5957 9.9468 -0.1341 -0.0064 -0.0636 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.414 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 + CLsurf = 0.00000 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 CDisurf = -0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.026 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.702 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.674 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.662 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.655 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.639 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.609 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.202 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.707 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.661 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.636 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.619 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.605 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.590 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.562 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.505 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.467 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.504 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.468 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_01_03.txt b/regression/scripts/AVL/avl_files/strip_forces_case_01_03.txt index e1645f466b..34c8272f09 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_01_03.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_01_03.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.17133 Clsurf = -0.03112 - CYsurf = -0.01139 Cmsurf = -0.14719 - CDsurf = 0.00311 Cnsurf = 0.00019 - CDisurf = 0.00311 CDvsurf = 0.00000 + CLsurf = 0.17194 Clsurf = -0.03118 + CYsurf = -0.01133 Cmsurf = -0.14753 + CDsurf = 0.00301 Cnsurf = 0.00019 + CDisurf = 0.00301 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.33515 CDsurf = 0.00607 + CLsurf = 0.33634 CDsurf = 0.00588 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 2.4800 0.0841 0.4057 0.3143 0.1674 0.0000 -0.0162 -0.0786 0.302 - 2 0.1025 7.6885 1.0492 2.3685 0.0835 0.3963 0.3070 0.0357 0.0000 -0.0163 -0.0762 0.303 - 3 0.2837 7.5620 1.7073 2.3560 0.0819 0.4012 0.3108 0.0273 0.0000 -0.0151 -0.0759 0.298 - 4 0.5530 7.3741 2.3052 2.3418 0.0792 0.4091 0.3169 0.0241 0.0000 -0.0133 -0.0757 0.292 - 5 0.9075 7.1267 2.8223 2.3147 0.0753 0.4186 0.3242 0.0211 0.0000 -0.0115 -0.0757 0.285 - 6 1.3432 6.8226 3.2414 2.2697 0.0701 0.4289 0.3322 0.0179 0.0000 -0.0099 -0.0761 0.280 - 7 1.8554 6.4651 3.5491 2.2043 0.0641 0.4397 0.3406 0.0159 0.0000 -0.0089 -0.0769 0.276 - 8 2.4386 6.0582 3.7368 2.1066 0.0569 0.4486 0.3475 0.0119 0.0000 -0.0088 -0.0782 0.275 - 9 3.0862 5.6062 3.8005 1.9835 0.0467 0.4566 0.3537 0.0083 0.0000 -0.0094 -0.0800 0.277 - 10 3.7613 5.1351 3.4440 1.8418 0.0360 0.4631 0.3587 0.0043 0.0000 -0.0112 -0.0824 0.281 - 11 4.4532 4.6522 3.3149 1.6924 0.0250 0.4699 0.3640 0.0012 0.0000 -0.0139 -0.0857 0.288 - 12 5.1831 4.1429 3.0930 1.5296 0.0097 0.4771 0.3695 -0.0030 0.0000 -0.0177 -0.0899 0.298 - 13 6.0123 3.7903 3.4706 1.3799 0.0005 0.4451 0.3644 -0.0044 0.0000 -0.0196 -0.0987 0.304 - 14 6.9353 3.6075 3.3775 1.2674 0.0021 0.4295 0.3517 -0.0031 0.0000 -0.0201 -0.0963 0.307 - 15 7.8737 3.4215 3.2389 1.1724 0.0025 0.4189 0.3430 -0.0025 0.0000 -0.0201 -0.0944 0.309 - 16 8.8172 3.2345 3.0619 1.0885 0.0028 0.4114 0.3368 -0.0021 0.0000 -0.0201 -0.0930 0.310 - 17 9.7556 3.0486 2.8543 1.0122 0.0033 0.4059 0.3323 -0.0019 0.0000 -0.0200 -0.0919 0.310 - 18 10.6786 2.8657 2.6240 0.9415 0.0040 0.4016 0.3288 -0.0018 0.0000 -0.0198 -0.0910 0.310 - 19 11.5760 2.6879 2.3787 0.8751 0.0049 0.3980 0.3258 -0.0017 0.0000 -0.0197 -0.0902 0.310 - 20 12.4328 2.5181 2.1010 0.8123 0.0060 0.3943 0.3228 -0.0016 0.0000 -0.0194 -0.0893 0.310 - 21 13.2400 2.3582 1.8520 0.7521 0.0074 0.3899 0.3192 -0.0015 0.0000 -0.0191 -0.0882 0.310 - 22 13.9941 2.2087 1.6074 0.6932 0.0095 0.3836 0.3141 -0.0014 0.0000 -0.0186 -0.0866 0.309 - 23 14.6868 2.0715 1.3716 0.6337 0.0123 0.3739 0.3062 -0.0013 0.0000 -0.0177 -0.0840 0.308 - 24 15.3105 1.9479 1.1479 0.5713 0.0159 0.3585 0.2935 -0.0011 0.0000 -0.0164 -0.0801 0.306 - 25 15.8583 1.8393 0.9381 0.5026 0.0202 0.3340 0.2735 -0.0007 0.0000 -0.0149 -0.0742 0.304 - 26 16.3244 1.7470 0.7427 0.4245 0.0248 0.2970 0.2432 0.0002 0.0000 -0.0145 -0.0671 0.310 - 27 16.6722 1.4928 0.4131 0.3400 0.0298 0.7667 0.2280 -0.0028 0.0000 -0.0133 -0.0333 0.308 - 28 16.9098 1.1466 0.2292 0.2535 0.0374 0.7447 0.2215 -0.0066 0.0000 -0.0039 -0.0282 0.268 - 29 17.0696 0.9138 0.1104 0.1577 0.0441 0.5817 0.1730 -0.0094 0.0000 0.0064 -0.0176 0.213 - 30 17.1499 0.7967 0.0322 0.0536 0.0477 0.2271 0.0675 -0.0065 0.0000 0.0059 -0.0053 0.163 + 1 0.0114 7.7520 0.3539 2.4964 0.0841 0.4084 0.3164 0.1675 0.0000 -0.0176 -0.0801 0.306 + 2 0.1025 7.6885 1.0491 2.3839 0.0835 0.3989 0.3090 0.0357 0.0000 -0.0175 -0.0776 0.307 + 3 0.2837 7.5620 1.7073 2.3714 0.0822 0.4039 0.3128 0.0273 0.0000 -0.0163 -0.0774 0.302 + 4 0.5530 7.3741 2.3052 2.3568 0.0798 0.4118 0.3190 0.0235 0.0000 -0.0146 -0.0772 0.296 + 5 0.9075 7.1267 2.8223 2.3305 0.0759 0.4215 0.3265 0.0213 0.0000 -0.0127 -0.0772 0.289 + 6 1.3432 6.8226 3.2414 2.2848 0.0706 0.4318 0.3345 0.0177 0.0000 -0.0112 -0.0776 0.283 + 7 1.8554 6.4651 3.5491 2.2149 0.0647 0.4419 0.3423 0.0129 0.0000 -0.0102 -0.0783 0.280 + 8 2.4386 6.0582 3.7368 2.1190 0.0576 0.4513 0.3496 0.0110 0.0000 -0.0098 -0.0795 0.278 + 9 3.0862 5.6062 3.8005 1.9960 0.0475 0.4595 0.3560 0.0081 0.0000 -0.0103 -0.0811 0.279 + 10 3.7613 5.1351 3.4440 1.8529 0.0366 0.4659 0.3609 0.0059 0.0000 -0.0116 -0.0832 0.282 + 11 4.4532 4.6522 3.3149 1.7014 0.0249 0.4724 0.3659 0.0010 0.0000 -0.0139 -0.0860 0.288 + 12 5.1831 4.1429 3.0930 1.5345 0.0091 0.4786 0.3707 -0.0030 0.0000 -0.0167 -0.0893 0.295 + 13 6.0123 3.7903 3.4706 1.3824 0.0001 0.4459 0.3651 -0.0044 0.0000 -0.0182 -0.0976 0.300 + 14 6.9353 3.6075 3.3775 1.2694 0.0018 0.4302 0.3522 -0.0031 0.0000 -0.0186 -0.0951 0.303 + 15 7.8737 3.4215 3.2389 1.1741 0.0023 0.4195 0.3434 -0.0025 0.0000 -0.0186 -0.0931 0.304 + 16 8.8172 3.2345 3.0619 1.0900 0.0027 0.4119 0.3373 -0.0022 0.0000 -0.0185 -0.0917 0.305 + 17 9.7556 3.0486 2.8543 1.0134 0.0032 0.4064 0.3327 -0.0019 0.0000 -0.0184 -0.0905 0.305 + 18 10.6786 2.8657 2.6239 0.9425 0.0039 0.4020 0.3292 -0.0018 0.0000 -0.0182 -0.0896 0.305 + 19 11.5760 2.6879 2.3787 0.8760 0.0048 0.3984 0.3262 -0.0017 0.0000 -0.0181 -0.0888 0.305 + 20 12.4328 2.5181 2.1010 0.8131 0.0059 0.3947 0.3231 -0.0016 0.0000 -0.0178 -0.0879 0.305 + 21 13.2400 2.3582 1.8520 0.7528 0.0074 0.3902 0.3195 -0.0015 0.0000 -0.0175 -0.0868 0.305 + 22 13.9941 2.2087 1.6074 0.6937 0.0094 0.3839 0.3143 -0.0014 0.0000 -0.0170 -0.0852 0.304 + 23 14.6868 2.0715 1.3716 0.6341 0.0122 0.3741 0.3063 -0.0013 0.0000 -0.0161 -0.0827 0.303 + 24 15.3105 1.9479 1.1479 0.5715 0.0159 0.3586 0.2936 -0.0011 0.0000 -0.0148 -0.0787 0.301 + 25 15.8583 1.8393 0.9381 0.5026 0.0202 0.3340 0.2734 -0.0007 0.0000 -0.0133 -0.0728 0.299 + 26 16.3244 1.7470 0.7427 0.4241 0.0246 0.2967 0.2429 0.0002 0.0000 -0.0129 -0.0657 0.303 + 27 16.6722 1.4928 0.4131 0.3396 0.0295 0.7658 0.2277 -0.0029 0.0000 -0.0120 -0.0327 0.303 + 28 16.9098 1.1466 0.2292 0.2534 0.0374 0.7443 0.2213 -0.0067 0.0000 -0.0029 -0.0277 0.263 + 29 17.0696 0.9138 0.1104 0.1577 0.0443 0.5818 0.1730 -0.0095 0.0000 0.0070 -0.0173 0.209 + 30 17.1499 0.7967 0.0322 0.0537 0.0484 0.2274 0.0676 -0.0066 0.0000 0.0061 -0.0052 0.160 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.17133 Clsurf = 0.03112 - CYsurf = 0.01139 Cmsurf = -0.14719 - CDsurf = 0.00311 Cnsurf = -0.00019 - CDisurf = 0.00311 CDvsurf = 0.00000 + CLsurf = 0.17194 Clsurf = 0.03118 + CYsurf = 0.01133 Cmsurf = -0.14753 + CDsurf = 0.00301 Cnsurf = -0.00019 + CDisurf = 0.00301 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.33515 CDsurf = 0.00606 + CLsurf = 0.33634 CDsurf = 0.00588 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 2.4800 0.0841 0.4057 0.3143 0.1674 0.0000 -0.0162 0.0786 0.302 - 32 -0.1025 7.6885 1.0492 2.3685 0.0834 0.3963 0.3070 0.0357 0.0000 -0.0163 0.0762 0.303 - 33 -0.2837 7.5620 1.7073 2.3560 0.0819 0.4012 0.3108 0.0273 0.0000 -0.0151 0.0759 0.298 - 34 -0.5530 7.3741 2.3052 2.3418 0.0792 0.4091 0.3169 0.0241 0.0000 -0.0133 0.0757 0.292 - 35 -0.9075 7.1267 2.8223 2.3147 0.0753 0.4186 0.3242 0.0211 0.0000 -0.0115 0.0757 0.285 - 36 -1.3432 6.8226 3.2414 2.2696 0.0701 0.4289 0.3322 0.0179 0.0000 -0.0099 0.0761 0.280 - 37 -1.8554 6.4651 3.5491 2.2043 0.0641 0.4397 0.3406 0.0159 0.0000 -0.0089 0.0769 0.276 - 38 -2.4386 6.0582 3.7368 2.1066 0.0569 0.4486 0.3475 0.0119 0.0000 -0.0088 0.0782 0.275 - 39 -3.0862 5.6062 3.8005 1.9835 0.0467 0.4566 0.3537 0.0083 0.0000 -0.0094 0.0800 0.277 - 40 -3.7613 5.1351 3.4440 1.8417 0.0360 0.4631 0.3587 0.0043 0.0000 -0.0112 0.0824 0.281 - 41 -4.4532 4.6522 3.3149 1.6924 0.0250 0.4699 0.3640 0.0012 0.0000 -0.0139 0.0857 0.288 - 42 -5.1831 4.1429 3.0930 1.5296 0.0097 0.4771 0.3695 -0.0030 0.0000 -0.0177 0.0899 0.298 - 43 -6.0123 3.7903 3.4706 1.3799 0.0005 0.4451 0.3644 -0.0044 0.0000 -0.0196 0.0987 0.304 - 44 -6.9353 3.6075 3.3775 1.2674 0.0020 0.4295 0.3516 -0.0031 0.0000 -0.0201 0.0963 0.307 - 45 -7.8737 3.4215 3.2389 1.1724 0.0025 0.4189 0.3430 -0.0025 0.0000 -0.0201 0.0944 0.309 - 46 -8.8172 3.2345 3.0619 1.0885 0.0028 0.4114 0.3368 -0.0021 0.0000 -0.0201 0.0930 0.310 - 47 -9.7556 3.0486 2.8543 1.0122 0.0033 0.4058 0.3323 -0.0019 0.0000 -0.0200 0.0918 0.310 - 48 -10.6786 2.8657 2.6240 0.9415 0.0040 0.4016 0.3288 -0.0018 0.0000 -0.0198 0.0910 0.310 - 49 -11.5760 2.6879 2.3787 0.8751 0.0049 0.3980 0.3258 -0.0017 0.0000 -0.0197 0.0902 0.310 - 50 -12.4328 2.5181 2.1010 0.8123 0.0060 0.3943 0.3228 -0.0016 0.0000 -0.0194 0.0893 0.310 - 51 -13.2400 2.3582 1.8520 0.7521 0.0074 0.3899 0.3192 -0.0015 0.0000 -0.0191 0.0882 0.310 - 52 -13.9941 2.2087 1.6074 0.6932 0.0095 0.3836 0.3141 -0.0014 0.0000 -0.0186 0.0866 0.309 - 53 -14.6868 2.0715 1.3716 0.6337 0.0123 0.3739 0.3061 -0.0013 0.0000 -0.0177 0.0840 0.308 - 54 -15.3105 1.9479 1.1479 0.5713 0.0159 0.3585 0.2935 -0.0011 0.0000 -0.0164 0.0801 0.306 - 55 -15.8583 1.8393 0.9381 0.5026 0.0202 0.3340 0.2735 -0.0007 0.0000 -0.0149 0.0742 0.304 - 56 -16.3244 1.7470 0.7427 0.4245 0.0248 0.2970 0.2432 0.0002 0.0000 -0.0145 0.0671 0.310 - 57 -16.6722 1.4928 0.4131 0.3400 0.0298 0.7667 0.2280 -0.0028 0.0000 -0.0133 0.0333 0.308 - 58 -16.9098 1.1466 0.2292 0.2535 0.0374 0.7447 0.2215 -0.0066 0.0000 -0.0039 0.0282 0.268 - 59 -17.0696 0.9138 0.1104 0.1577 0.0441 0.5817 0.1730 -0.0094 0.0000 0.0064 0.0176 0.213 - 60 -17.1499 0.7967 0.0322 0.0536 0.0477 0.2271 0.0675 -0.0065 0.0000 0.0059 0.0053 0.163 + 31 -0.0114 7.7520 0.3539 2.4964 0.0840 0.4084 0.3164 0.1675 0.0000 -0.0176 0.0801 0.306 + 32 -0.1025 7.6885 1.0491 2.3839 0.0835 0.3989 0.3090 0.0357 0.0000 -0.0175 0.0776 0.307 + 33 -0.2837 7.5620 1.7073 2.3714 0.0822 0.4039 0.3128 0.0273 0.0000 -0.0163 0.0774 0.302 + 34 -0.5530 7.3741 2.3052 2.3568 0.0798 0.4118 0.3190 0.0235 0.0000 -0.0146 0.0772 0.296 + 35 -0.9075 7.1267 2.8223 2.3305 0.0759 0.4215 0.3265 0.0213 0.0000 -0.0127 0.0772 0.289 + 36 -1.3432 6.8226 3.2414 2.2848 0.0706 0.4318 0.3345 0.0177 0.0000 -0.0112 0.0776 0.283 + 37 -1.8554 6.4651 3.5491 2.2149 0.0647 0.4419 0.3423 0.0129 0.0000 -0.0102 0.0783 0.280 + 38 -2.4386 6.0582 3.7368 2.1190 0.0576 0.4513 0.3496 0.0110 0.0000 -0.0098 0.0795 0.278 + 39 -3.0862 5.6062 3.8005 1.9960 0.0475 0.4595 0.3560 0.0081 0.0000 -0.0103 0.0811 0.279 + 40 -3.7613 5.1351 3.4440 1.8529 0.0366 0.4659 0.3609 0.0059 0.0000 -0.0116 0.0832 0.282 + 41 -4.4532 4.6522 3.3149 1.7014 0.0249 0.4724 0.3659 0.0010 0.0000 -0.0139 0.0860 0.288 + 42 -5.1831 4.1429 3.0930 1.5345 0.0091 0.4786 0.3707 -0.0030 0.0000 -0.0167 0.0893 0.295 + 43 -6.0123 3.7903 3.4706 1.3823 0.0001 0.4459 0.3651 -0.0044 0.0000 -0.0182 0.0976 0.300 + 44 -6.9353 3.6075 3.3775 1.2694 0.0018 0.4302 0.3522 -0.0031 0.0000 -0.0186 0.0951 0.303 + 45 -7.8737 3.4215 3.2389 1.1741 0.0023 0.4195 0.3434 -0.0025 0.0000 -0.0186 0.0931 0.304 + 46 -8.8172 3.2345 3.0619 1.0900 0.0027 0.4119 0.3373 -0.0022 0.0000 -0.0185 0.0917 0.305 + 47 -9.7556 3.0486 2.8543 1.0134 0.0032 0.4064 0.3327 -0.0019 0.0000 -0.0184 0.0905 0.305 + 48 -10.6786 2.8657 2.6239 0.9425 0.0039 0.4020 0.3292 -0.0018 0.0000 -0.0182 0.0896 0.305 + 49 -11.5760 2.6879 2.3787 0.8760 0.0048 0.3984 0.3262 -0.0017 0.0000 -0.0181 0.0888 0.305 + 50 -12.4328 2.5181 2.1010 0.8131 0.0059 0.3947 0.3231 -0.0016 0.0000 -0.0178 0.0879 0.305 + 51 -13.2400 2.3582 1.8520 0.7528 0.0074 0.3902 0.3195 -0.0015 0.0000 -0.0175 0.0868 0.305 + 52 -13.9941 2.2087 1.6074 0.6937 0.0094 0.3839 0.3143 -0.0014 0.0000 -0.0170 0.0852 0.304 + 53 -14.6868 2.0715 1.3716 0.6341 0.0122 0.3741 0.3063 -0.0013 0.0000 -0.0161 0.0827 0.303 + 54 -15.3105 1.9479 1.1479 0.5715 0.0159 0.3586 0.2936 -0.0011 0.0000 -0.0148 0.0787 0.301 + 55 -15.8583 1.8393 0.9381 0.5026 0.0202 0.3340 0.2734 -0.0007 0.0000 -0.0133 0.0728 0.299 + 56 -16.3244 1.7470 0.7427 0.4241 0.0246 0.2967 0.2429 0.0002 0.0000 -0.0129 0.0657 0.303 + 57 -16.6722 1.4928 0.4131 0.3396 0.0295 0.7658 0.2277 -0.0029 0.0000 -0.0120 0.0327 0.303 + 58 -16.9098 1.1466 0.2292 0.2534 0.0374 0.7443 0.2213 -0.0067 0.0000 -0.0029 0.0277 0.263 + 59 -17.0696 0.9138 0.1104 0.1577 0.0443 0.5818 0.1730 -0.0095 0.0000 0.0070 0.0173 0.209 + 60 -17.1499 0.7967 0.0322 0.0537 0.0484 0.2274 0.0676 -0.0066 0.0000 0.0061 0.0052 0.160 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00309 Clsurf = -0.00046 - CYsurf = -0.00049 Cmsurf = -0.01570 - CDsurf = 0.00008 Cnsurf = 0.00030 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00296 Clsurf = -0.00045 + CYsurf = -0.00046 Cmsurf = -0.01507 + CDsurf = 0.00008 Cnsurf = 0.00029 CDisurf = 0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01885 CDsurf = 0.00051 + CLsurf = 0.01805 CDsurf = 0.00049 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.0066 0.0424 0.0020 0.0015 0.0001 0.0000 -0.0011 -0.0013 0.984 - 62 0.0418 4.2566 0.2392 0.0066 0.0423 0.0020 0.0015 0.0001 0.0000 -0.0011 -0.0013 0.985 - 63 0.1156 4.2274 0.3930 0.0066 0.0422 0.0020 0.0016 0.0001 0.0000 -0.0011 -0.0013 0.977 - 64 0.2254 4.1839 0.5386 0.0068 0.0418 0.0021 0.0016 0.0001 0.0000 -0.0011 -0.0013 0.953 - 65 0.3698 4.1268 0.6730 0.0072 0.0413 0.0023 0.0017 0.0001 0.0000 -0.0012 -0.0013 0.910 - 66 0.5474 4.0565 0.7936 0.0079 0.0405 0.0025 0.0019 0.0001 0.0000 -0.0012 -0.0014 0.846 - 67 0.7617 3.9717 0.9441 0.0090 0.0395 0.0029 0.0023 0.0001 0.0000 -0.0012 -0.0015 0.765 - 68 1.0116 3.8728 1.0344 0.0108 0.0383 0.0036 0.0028 0.0001 0.0000 -0.0012 -0.0016 0.673 - 69 1.2891 3.7630 1.1046 0.0134 0.0369 0.0046 0.0036 0.0001 0.0000 -0.0012 -0.0018 0.583 - 70 1.5912 3.6435 1.1542 0.0171 0.0355 0.0061 0.0047 0.0002 0.0000 -0.0012 -0.0020 0.504 - 71 1.9146 3.5155 1.1831 0.0220 0.0340 0.0081 0.0063 0.0002 0.0000 -0.0012 -0.0023 0.438 - 72 2.2558 3.3805 1.1921 0.0283 0.0326 0.0109 0.0084 0.0003 0.0000 -0.0011 -0.0028 0.387 - 73 2.6109 3.2400 1.1821 0.0359 0.0312 0.0144 0.0111 0.0004 0.0000 -0.0011 -0.0033 0.349 - 74 2.9762 3.0955 1.1548 0.0446 0.0299 0.0187 0.0144 0.0005 0.0000 -0.0010 -0.0039 0.320 - 75 3.3476 2.9485 1.1122 0.0541 0.0287 0.0238 0.0183 0.0006 0.0000 -0.0009 -0.0047 0.298 - 76 3.7210 2.8008 1.0564 0.0638 0.0277 0.0295 0.0228 0.0007 0.0000 -0.0007 -0.0055 0.282 - 77 4.0924 2.6538 0.9900 0.0732 0.0268 0.0358 0.0276 0.0008 0.0000 -0.0006 -0.0063 0.270 - 78 4.4577 2.5093 0.9155 0.0818 0.0262 0.0423 0.0326 0.0009 0.0000 -0.0003 -0.0072 0.261 - 79 4.8128 2.3687 0.8353 0.0891 0.0257 0.0488 0.0376 0.0010 0.0000 -0.0001 -0.0081 0.253 - 80 5.1540 2.2338 0.7518 0.0946 0.0255 0.0549 0.0423 0.0011 0.0000 0.0002 -0.0089 0.245 - 81 5.4774 2.1058 0.6671 0.0979 0.0255 0.0603 0.0465 0.0012 0.0000 0.0005 -0.0094 0.238 - 82 5.7795 1.9862 0.5830 0.0988 0.0257 0.0645 0.0498 0.0012 0.0000 0.0010 -0.0098 0.231 - 83 6.0570 1.8764 0.5012 0.0973 0.0260 0.0672 0.0518 0.0012 0.0000 0.0015 -0.0098 0.222 - 84 6.3069 1.7776 0.4225 0.0931 0.0265 0.0679 0.0524 0.0011 0.0000 0.0020 -0.0094 0.211 - 85 6.5264 1.6907 0.3478 0.0864 0.0270 0.0663 0.0511 0.0011 0.0000 0.0027 -0.0087 0.198 - 86 6.7314 1.6096 0.3326 0.0767 0.0275 0.0618 0.0477 0.0009 0.0000 0.0032 -0.0074 0.182 - 87 6.9144 1.5372 0.2507 0.0634 0.0281 0.0535 0.0412 0.0007 0.0000 0.0036 -0.0057 0.162 - 88 7.0535 1.4822 0.1746 0.0473 0.0286 0.0414 0.0319 0.0005 0.0000 0.0035 -0.0039 0.141 - 89 7.1471 1.4451 0.1029 0.0292 0.0289 0.0262 0.0202 0.0003 0.0000 0.0026 -0.0021 0.122 - 90 7.1941 1.4265 0.0340 0.0099 0.0290 0.0090 0.0069 0.0000 0.0000 0.0010 -0.0007 0.111 + 61 0.0047 4.2713 0.0803 0.0027 0.0425 0.0008 0.0006 0.0000 0.0000 -0.0011 -0.0011 + 62 0.0418 4.2566 0.2392 0.0027 0.0424 0.0008 0.0006 0.0000 0.0000 -0.0011 -0.0011 + 63 0.1156 4.2274 0.3930 0.0027 0.0423 0.0008 0.0006 0.0000 0.0000 -0.0011 -0.0011 1.978 + 64 0.2254 4.1839 0.5386 0.0029 0.0419 0.0009 0.0007 0.0000 0.0000 -0.0011 -0.0011 1.865 + 65 0.3698 4.1268 0.6730 0.0033 0.0414 0.0010 0.0008 0.0000 0.0000 -0.0011 -0.0011 1.670 + 66 0.5474 4.0565 0.7936 0.0040 0.0406 0.0013 0.0010 0.0000 0.0000 -0.0011 -0.0012 1.417 + 67 0.7617 3.9717 0.9441 0.0051 0.0396 0.0017 0.0013 0.0000 0.0000 -0.0012 -0.0013 1.149 + 68 1.0116 3.8728 1.0344 0.0069 0.0384 0.0023 0.0018 0.0001 0.0000 -0.0012 -0.0014 0.906 + 69 1.2891 3.7630 1.1046 0.0096 0.0370 0.0033 0.0026 0.0001 0.0000 -0.0012 -0.0015 0.715 + 70 1.5912 3.6435 1.1542 0.0134 0.0356 0.0048 0.0037 0.0001 0.0000 -0.0012 -0.0018 0.575 + 71 1.9146 3.5155 1.1831 0.0185 0.0341 0.0068 0.0053 0.0002 0.0000 -0.0012 -0.0021 0.476 + 72 2.2558 3.3805 1.1921 0.0250 0.0327 0.0096 0.0074 0.0003 0.0000 -0.0012 -0.0026 0.407 + 73 2.6109 3.2400 1.1821 0.0328 0.0313 0.0131 0.0101 0.0003 0.0000 -0.0011 -0.0031 0.360 + 74 2.9762 3.0955 1.1548 0.0418 0.0300 0.0175 0.0135 0.0005 0.0000 -0.0010 -0.0037 0.326 + 75 3.3476 2.9485 1.1122 0.0515 0.0288 0.0226 0.0175 0.0006 0.0000 -0.0009 -0.0045 0.302 + 76 3.7210 2.8008 1.0564 0.0615 0.0278 0.0285 0.0219 0.0007 0.0000 -0.0008 -0.0053 0.284 + 77 4.0924 2.6538 0.9900 0.0712 0.0269 0.0348 0.0268 0.0008 0.0000 -0.0006 -0.0062 0.271 + 78 4.4577 2.5093 0.9155 0.0801 0.0263 0.0414 0.0319 0.0009 0.0000 -0.0004 -0.0071 0.261 + 79 4.8128 2.3687 0.8353 0.0876 0.0258 0.0480 0.0370 0.0010 0.0000 -0.0001 -0.0080 0.253 + 80 5.1540 2.2338 0.7518 0.0933 0.0256 0.0542 0.0418 0.0011 0.0000 0.0002 -0.0087 0.245 + 81 5.4774 2.1058 0.6671 0.0969 0.0255 0.0596 0.0460 0.0012 0.0000 0.0005 -0.0094 0.238 + 82 5.7795 1.9862 0.5830 0.0980 0.0257 0.0640 0.0493 0.0012 0.0000 0.0010 -0.0097 0.231 + 83 6.0570 1.8764 0.5012 0.0966 0.0260 0.0667 0.0515 0.0012 0.0000 0.0015 -0.0097 0.222 + 84 6.3069 1.7776 0.4225 0.0926 0.0265 0.0675 0.0521 0.0011 0.0000 0.0020 -0.0094 0.211 + 85 6.5264 1.6907 0.3478 0.0859 0.0270 0.0659 0.0508 0.0011 0.0000 0.0026 -0.0086 0.198 + 86 6.7314 1.6096 0.3326 0.0764 0.0276 0.0616 0.0475 0.0009 0.0000 0.0032 -0.0074 0.182 + 87 6.9144 1.5372 0.2507 0.0631 0.0281 0.0532 0.0411 0.0007 0.0000 0.0036 -0.0057 0.162 + 88 7.0535 1.4822 0.1746 0.0471 0.0286 0.0412 0.0318 0.0005 0.0000 0.0035 -0.0038 0.140 + 89 7.1471 1.4451 0.1029 0.0291 0.0289 0.0261 0.0201 0.0003 0.0000 0.0026 -0.0021 0.122 + 90 7.1941 1.4265 0.0340 0.0098 0.0291 0.0090 0.0069 0.0000 0.0000 0.0010 -0.0007 0.110 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00309 Clsurf = 0.00046 - CYsurf = 0.00049 Cmsurf = -0.01570 - CDsurf = 0.00008 Cnsurf = -0.00030 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00296 Clsurf = 0.00045 + CYsurf = 0.00046 Cmsurf = -0.01507 + CDsurf = 0.00008 Cnsurf = -0.00029 CDisurf = 0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01885 CDsurf = 0.00051 + CLsurf = 0.01805 CDsurf = 0.00049 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.0066 0.0424 0.0020 0.0015 0.0001 0.0000 -0.0011 0.0013 0.984 - 92 -0.0418 4.2566 0.2392 0.0066 0.0423 0.0020 0.0015 0.0001 0.0000 -0.0011 0.0013 0.985 - 93 -0.1156 4.2274 0.3930 0.0066 0.0422 0.0020 0.0016 0.0001 0.0000 -0.0011 0.0013 0.977 - 94 -0.2254 4.1839 0.5386 0.0068 0.0418 0.0021 0.0016 0.0001 0.0000 -0.0011 0.0013 0.953 - 95 -0.3698 4.1268 0.6730 0.0072 0.0413 0.0023 0.0017 0.0001 0.0000 -0.0012 0.0013 0.910 - 96 -0.5474 4.0565 0.7936 0.0079 0.0405 0.0025 0.0019 0.0001 0.0000 -0.0012 0.0014 0.846 - 97 -0.7617 3.9717 0.9441 0.0090 0.0395 0.0029 0.0023 0.0001 0.0000 -0.0012 0.0015 0.765 - 98 -1.0116 3.8728 1.0344 0.0108 0.0383 0.0036 0.0028 0.0001 0.0000 -0.0012 0.0016 0.673 - 99 -1.2891 3.7630 1.1046 0.0134 0.0369 0.0046 0.0036 0.0001 0.0000 -0.0012 0.0018 0.583 - 100 -1.5912 3.6435 1.1542 0.0171 0.0355 0.0061 0.0047 0.0002 0.0000 -0.0012 0.0020 0.504 - 101 -1.9146 3.5155 1.1831 0.0220 0.0340 0.0081 0.0063 0.0002 0.0000 -0.0012 0.0023 0.438 - 102 -2.2558 3.3805 1.1921 0.0283 0.0326 0.0109 0.0084 0.0003 0.0000 -0.0011 0.0028 0.387 - 103 -2.6109 3.2400 1.1821 0.0359 0.0312 0.0144 0.0111 0.0004 0.0000 -0.0011 0.0033 0.349 - 104 -2.9762 3.0955 1.1548 0.0446 0.0299 0.0187 0.0144 0.0005 0.0000 -0.0010 0.0039 0.320 - 105 -3.3476 2.9485 1.1122 0.0541 0.0287 0.0238 0.0183 0.0006 0.0000 -0.0009 0.0047 0.298 - 106 -3.7210 2.8008 1.0564 0.0638 0.0277 0.0295 0.0228 0.0007 0.0000 -0.0007 0.0055 0.282 - 107 -4.0924 2.6538 0.9900 0.0732 0.0268 0.0358 0.0276 0.0008 0.0000 -0.0006 0.0063 0.270 - 108 -4.4577 2.5093 0.9155 0.0818 0.0262 0.0423 0.0326 0.0009 0.0000 -0.0003 0.0072 0.261 - 109 -4.8128 2.3687 0.8353 0.0891 0.0257 0.0488 0.0376 0.0010 0.0000 -0.0001 0.0081 0.253 - 110 -5.1540 2.2338 0.7518 0.0946 0.0255 0.0549 0.0423 0.0011 0.0000 0.0002 0.0089 0.245 - 111 -5.4774 2.1058 0.6671 0.0979 0.0255 0.0603 0.0465 0.0012 0.0000 0.0005 0.0094 0.238 - 112 -5.7795 1.9862 0.5830 0.0988 0.0257 0.0645 0.0498 0.0012 0.0000 0.0010 0.0098 0.231 - 113 -6.0570 1.8764 0.5012 0.0973 0.0260 0.0672 0.0518 0.0012 0.0000 0.0015 0.0098 0.222 - 114 -6.3069 1.7776 0.4225 0.0931 0.0265 0.0679 0.0524 0.0011 0.0000 0.0020 0.0094 0.211 - 115 -6.5264 1.6907 0.3478 0.0864 0.0270 0.0663 0.0511 0.0011 0.0000 0.0027 0.0087 0.198 - 116 -6.7314 1.6096 0.3326 0.0767 0.0275 0.0618 0.0477 0.0009 0.0000 0.0032 0.0074 0.182 - 117 -6.9144 1.5372 0.2507 0.0634 0.0281 0.0535 0.0412 0.0007 0.0000 0.0036 0.0057 0.162 - 118 -7.0535 1.4822 0.1746 0.0473 0.0286 0.0414 0.0319 0.0005 0.0000 0.0035 0.0039 0.141 - 119 -7.1471 1.4451 0.1029 0.0292 0.0289 0.0262 0.0202 0.0003 0.0000 0.0026 0.0021 0.122 - 120 -7.1941 1.4265 0.0340 0.0099 0.0290 0.0090 0.0069 0.0000 0.0000 0.0010 0.0007 0.111 + 91 -0.0047 4.2713 0.0803 0.0027 0.0425 0.0008 0.0006 0.0000 0.0000 -0.0011 0.0011 + 92 -0.0418 4.2566 0.2392 0.0027 0.0424 0.0008 0.0006 0.0000 0.0000 -0.0011 0.0011 + 93 -0.1156 4.2274 0.3930 0.0027 0.0423 0.0008 0.0006 0.0000 0.0000 -0.0011 0.0011 1.978 + 94 -0.2254 4.1839 0.5386 0.0029 0.0419 0.0009 0.0007 0.0000 0.0000 -0.0011 0.0011 1.865 + 95 -0.3698 4.1268 0.6730 0.0033 0.0414 0.0010 0.0008 0.0000 0.0000 -0.0011 0.0011 1.670 + 96 -0.5474 4.0565 0.7936 0.0040 0.0406 0.0013 0.0010 0.0000 0.0000 -0.0011 0.0012 1.417 + 97 -0.7617 3.9717 0.9441 0.0051 0.0396 0.0017 0.0013 0.0000 0.0000 -0.0012 0.0013 1.149 + 98 -1.0116 3.8728 1.0344 0.0069 0.0384 0.0023 0.0018 0.0001 0.0000 -0.0012 0.0014 0.906 + 99 -1.2891 3.7630 1.1046 0.0096 0.0370 0.0033 0.0026 0.0001 0.0000 -0.0012 0.0015 0.715 + 100 -1.5912 3.6435 1.1542 0.0134 0.0356 0.0048 0.0037 0.0001 0.0000 -0.0012 0.0018 0.575 + 101 -1.9146 3.5155 1.1831 0.0185 0.0341 0.0068 0.0053 0.0002 0.0000 -0.0012 0.0021 0.476 + 102 -2.2558 3.3805 1.1921 0.0250 0.0327 0.0096 0.0074 0.0003 0.0000 -0.0012 0.0026 0.407 + 103 -2.6109 3.2400 1.1821 0.0328 0.0313 0.0131 0.0101 0.0003 0.0000 -0.0011 0.0031 0.360 + 104 -2.9762 3.0955 1.1548 0.0418 0.0300 0.0175 0.0135 0.0005 0.0000 -0.0010 0.0037 0.326 + 105 -3.3476 2.9485 1.1122 0.0515 0.0288 0.0226 0.0175 0.0006 0.0000 -0.0009 0.0045 0.302 + 106 -3.7210 2.8008 1.0564 0.0615 0.0278 0.0285 0.0219 0.0007 0.0000 -0.0008 0.0053 0.284 + 107 -4.0924 2.6538 0.9900 0.0712 0.0269 0.0348 0.0268 0.0008 0.0000 -0.0006 0.0062 0.271 + 108 -4.4577 2.5093 0.9155 0.0801 0.0263 0.0414 0.0319 0.0009 0.0000 -0.0004 0.0071 0.261 + 109 -4.8128 2.3687 0.8353 0.0876 0.0258 0.0480 0.0370 0.0010 0.0000 -0.0001 0.0080 0.253 + 110 -5.1540 2.2338 0.7518 0.0933 0.0256 0.0542 0.0418 0.0011 0.0000 0.0002 0.0087 0.245 + 111 -5.4774 2.1058 0.6671 0.0969 0.0255 0.0596 0.0460 0.0012 0.0000 0.0005 0.0094 0.238 + 112 -5.7795 1.9862 0.5830 0.0980 0.0257 0.0640 0.0493 0.0012 0.0000 0.0010 0.0097 0.231 + 113 -6.0570 1.8764 0.5012 0.0966 0.0260 0.0667 0.0515 0.0012 0.0000 0.0015 0.0097 0.222 + 114 -6.3069 1.7776 0.4225 0.0926 0.0265 0.0675 0.0521 0.0011 0.0000 0.0020 0.0094 0.211 + 115 -6.5264 1.6907 0.3478 0.0859 0.0270 0.0659 0.0508 0.0011 0.0000 0.0026 0.0086 0.198 + 116 -6.7314 1.6096 0.3326 0.0764 0.0276 0.0616 0.0475 0.0009 0.0000 0.0032 0.0074 0.182 + 117 -6.9144 1.5372 0.2507 0.0631 0.0281 0.0532 0.0411 0.0007 0.0000 0.0036 0.0057 0.162 + 118 -7.0535 1.4822 0.1746 0.0471 0.0286 0.0412 0.0318 0.0005 0.0000 0.0035 0.0038 0.140 + 119 -7.1471 1.4451 0.1029 0.0291 0.0289 0.0261 0.0201 0.0003 0.0000 0.0026 0.0021 0.122 + 120 -7.1941 1.4265 0.0340 0.0098 0.0291 0.0090 0.0069 0.0000 0.0000 0.0010 0.0007 0.110 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.210 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.246 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 + 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.229 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.238 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.214 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 129 0.0000 5.8609 2.1733 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 131 0.0000 4.4389 1.6667 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.195 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.210 + 134 0.0000 3.7615 1.5362 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.214 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.206 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.191 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.172 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.151 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.135 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.122 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.215 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.203 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.186 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.168 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.147 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.128 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.119 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00045 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.01678 + CLsurf = -0.00052 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.01685 CDsurf = -0.00012 Cnsurf = -0.00000 CDisurf = -0.00012 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00045 CDsurf = -0.00012 + CLsurf = -0.00052 CDsurf = -0.00012 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.0226 0.0466 -0.0103 -0.0008 -0.0006 0.0000 0.0020 0.0003 - 152 -1.3090 31.2096 11.6724 -0.0206 0.0548 -0.0025 -0.0007 -0.0002 0.0000 0.0022 0.0006 - 153 -0.9350 34.0626 12.7394 -0.0153 0.0604 -0.0011 -0.0004 -0.0001 0.0000 0.0023 0.0008 - 154 -0.5610 36.1619 13.5246 -0.0100 0.0645 -0.0005 -0.0003 0.0000 0.0000 0.0022 0.0010 - 155 -0.1870 37.5332 14.0374 -0.0067 0.0671 -0.0002 -0.0002 0.0001 0.0000 0.0022 0.0016 - 156 0.1870 37.5332 14.0374 -0.0067 0.0671 -0.0002 -0.0002 0.0001 0.0000 0.0022 0.0016 - 157 0.5610 36.1619 13.5246 -0.0100 0.0645 -0.0005 -0.0003 0.0000 0.0000 0.0022 0.0010 - 158 0.9350 34.0626 12.7394 -0.0153 0.0604 -0.0011 -0.0004 -0.0001 0.0000 0.0023 0.0008 - 159 1.3090 31.2096 11.6724 -0.0206 0.0548 -0.0025 -0.0007 -0.0002 0.0000 0.0022 0.0006 - 160 1.6830 26.5957 9.9468 -0.0226 0.0466 -0.0103 -0.0008 -0.0006 0.0000 0.0020 0.0003 + 151 -1.6830 26.5957 9.9468 -0.0243 0.0465 -0.0111 -0.0009 -0.0006 0.0000 0.0020 0.0003 + 152 -1.3090 31.2096 11.6724 -0.0229 0.0548 -0.0028 -0.0007 -0.0002 0.0000 0.0022 0.0006 + 153 -0.9350 34.0626 12.7394 -0.0178 0.0606 -0.0013 -0.0005 -0.0001 0.0000 0.0023 0.0008 + 154 -0.5610 36.1619 13.5246 -0.0125 0.0648 -0.0006 -0.0003 0.0000 0.0000 0.0023 0.0011 + 155 -0.1870 37.5332 14.0374 -0.0092 0.0673 -0.0003 -0.0003 0.0001 0.0000 0.0022 0.0016 + 156 0.1870 37.5332 14.0374 -0.0092 0.0673 -0.0003 -0.0003 0.0001 0.0000 0.0022 0.0016 + 157 0.5610 36.1619 13.5246 -0.0125 0.0648 -0.0006 -0.0003 0.0000 0.0000 0.0023 0.0011 + 158 0.9350 34.0626 12.7394 -0.0178 0.0606 -0.0013 -0.0005 -0.0001 0.0000 0.0023 0.0008 + 159 1.3090 31.2096 11.6724 -0.0229 0.0548 -0.0028 -0.0007 -0.0002 0.0000 0.0022 0.0006 + 160 1.6830 26.5957 9.9468 -0.0243 0.0465 -0.0111 -0.0009 -0.0006 0.0000 0.0020 0.0003 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = 0.00000 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = -0.00000 Cnsurf = -0.00000 - CDisurf = -0.00000 CDvsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 + CDsurf = 0.00000 Cnsurf = -0.00000 + CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = 0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.469 - 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.461 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.471 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.493 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.537 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.536 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.535 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.541 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.584 + 161 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 1.463 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.525 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.487 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.481 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.483 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.533 + 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.553 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.557 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.559 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.592 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_01_04.txt b/regression/scripts/AVL/avl_files/strip_forces_case_01_04.txt index 74f1b6c2e5..8b55672672 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_01_04.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_01_04.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.29266 Clsurf = -0.05607 - CYsurf = -0.01744 Cmsurf = -0.25972 - CDsurf = 0.00791 Cnsurf = -0.00304 - CDisurf = 0.00791 CDvsurf = 0.00000 + CLsurf = 0.29329 Clsurf = -0.05613 + CYsurf = -0.01729 Cmsurf = -0.26006 + CDsurf = 0.00766 Cnsurf = -0.00306 + CDisurf = 0.00766 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.57224 CDsurf = 0.01545 + CLsurf = 0.57344 CDsurf = 0.01496 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 3.8692 0.1377 0.6039 0.4675 0.3827 0.0000 -0.0250 -0.1228 0.304 - 2 0.1025 7.6885 1.0492 3.6117 0.1372 0.6003 0.4647 0.0783 0.0000 -0.0252 -0.1170 0.304 - 3 0.2837 7.5620 1.7073 3.5879 0.1358 0.6085 0.4711 0.0591 0.0000 -0.0233 -0.1164 0.300 - 4 0.5530 7.3741 2.3052 3.5700 0.1329 0.6218 0.4814 0.0527 0.0000 -0.0205 -0.1161 0.293 - 5 0.9075 7.1267 2.8223 3.5377 0.1278 0.6384 0.4942 0.0466 0.0000 -0.0175 -0.1162 0.285 - 6 1.3432 6.8226 3.2414 3.4854 0.1180 0.6579 0.5093 0.0404 0.0000 -0.0149 -0.1170 0.279 - 7 1.8554 6.4651 3.5491 3.4125 0.1004 0.6803 0.5266 0.0368 0.0000 -0.0127 -0.1188 0.274 - 8 2.4386 6.0582 3.7368 3.2951 0.0822 0.7020 0.5434 0.0289 0.0000 -0.0119 -0.1214 0.272 - 9 3.0862 5.6062 3.8005 3.1487 0.0699 0.7258 0.5619 0.0220 0.0000 -0.0120 -0.1251 0.271 - 10 3.7613 5.1351 3.4440 2.9768 0.0585 0.7501 0.5807 0.0140 0.0000 -0.0134 -0.1299 0.273 - 11 4.4532 4.6522 3.3149 2.7960 0.0456 0.7785 0.6026 0.0076 0.0000 -0.0158 -0.1363 0.276 - 12 5.1831 4.1429 3.0930 2.5920 0.0266 0.8115 0.6282 -0.0017 0.0000 -0.0190 -0.1439 0.280 - 13 6.0123 3.7903 3.4706 2.3972 0.0143 0.7786 0.6353 -0.0053 0.0000 -0.0188 -0.1590 0.280 - 14 6.9353 3.6075 3.3775 2.2448 0.0138 0.7658 0.6249 -0.0032 0.0000 -0.0192 -0.1570 0.281 - 15 7.8737 3.4215 3.2389 2.1100 0.0119 0.7589 0.6193 -0.0026 0.0000 -0.0192 -0.1557 0.281 - 16 8.8172 3.2345 3.0619 1.9851 0.0107 0.7552 0.6163 -0.0025 0.0000 -0.0190 -0.1550 0.281 - 17 9.7556 3.0486 2.8543 1.8662 0.0106 0.7533 0.6147 -0.0025 0.0000 -0.0188 -0.1544 0.281 - 18 10.6786 2.8657 2.6240 1.7515 0.0115 0.7521 0.6138 -0.0026 0.0000 -0.0186 -0.1540 0.280 - 19 11.5760 2.6879 2.3787 1.6402 0.0128 0.7510 0.6128 -0.0028 0.0000 -0.0183 -0.1536 0.280 - 20 12.4328 2.5181 2.1010 1.5318 0.0148 0.7486 0.6109 -0.0030 0.0000 -0.0179 -0.1528 0.279 - 21 13.2400 2.3582 1.8520 1.4251 0.0175 0.7437 0.6069 -0.0030 0.0000 -0.0173 -0.1513 0.278 - 22 13.9941 2.2087 1.6074 1.3182 0.0213 0.7345 0.5993 -0.0030 0.0000 -0.0163 -0.1487 0.277 - 23 14.6868 2.0715 1.3716 1.2081 0.0266 0.7178 0.5857 -0.0028 0.0000 -0.0146 -0.1442 0.275 - 24 15.3105 1.9479 1.1479 1.0906 0.0334 0.6890 0.5622 -0.0024 0.0000 -0.0122 -0.1368 0.272 - 25 15.8583 1.8393 0.9381 0.9592 0.0412 0.6417 0.5236 -0.0013 0.0000 -0.0095 -0.1258 0.268 - 26 16.3244 1.7470 0.7427 0.8089 0.0493 0.5694 0.4646 0.0022 0.0000 -0.0102 -0.1132 0.272 - 27 16.6722 1.4928 0.4131 0.6458 0.0579 1.4642 0.4352 -0.0109 0.0000 -0.0110 -0.0581 0.275 - 28 16.9098 1.1466 0.2292 0.4795 0.0702 1.4196 0.4220 -0.0256 0.0000 0.0061 -0.0485 0.236 - 29 17.0696 0.9138 0.1104 0.2969 0.0805 1.1080 0.3294 -0.0368 0.0000 0.0231 -0.0292 0.180 - 30 17.1499 0.7967 0.0322 0.1006 0.0859 0.4346 0.1292 -0.0270 0.0000 0.0159 -0.0082 0.127 + 1 0.0114 7.7520 0.3539 3.8862 0.1377 0.6067 0.4697 0.3830 0.0000 -0.0265 -0.1244 0.306 + 2 0.1025 7.6885 1.0491 3.6270 0.1373 0.6028 0.4667 0.0782 0.0000 -0.0265 -0.1184 0.307 + 3 0.2837 7.5620 1.7073 3.6032 0.1361 0.6112 0.4731 0.0591 0.0000 -0.0246 -0.1179 0.302 + 4 0.5530 7.3741 2.3052 3.5841 0.1335 0.6244 0.4834 0.0511 0.0000 -0.0218 -0.1175 0.295 + 5 0.9075 7.1267 2.8223 3.5537 0.1284 0.6412 0.4964 0.0470 0.0000 -0.0188 -0.1177 0.288 + 6 1.3432 6.8226 3.2414 3.5001 0.1186 0.6607 0.5115 0.0396 0.0000 -0.0161 -0.1185 0.282 + 7 1.8554 6.4651 3.5491 3.4176 0.1010 0.6821 0.5280 0.0297 0.0000 -0.0142 -0.1201 0.277 + 8 2.4386 6.0582 3.7368 3.3055 0.0828 0.7045 0.5454 0.0266 0.0000 -0.0130 -0.1226 0.274 + 9 3.0862 5.6062 3.8005 3.1609 0.0707 0.7287 0.5641 0.0214 0.0000 -0.0129 -0.1263 0.273 + 10 3.7613 5.1351 3.4440 2.9890 0.0591 0.7528 0.5828 0.0175 0.0000 -0.0139 -0.1308 0.274 + 11 4.4532 4.6522 3.3149 2.8078 0.0456 0.7818 0.6052 0.0070 0.0000 -0.0159 -0.1369 0.276 + 12 5.1831 4.1429 3.0930 2.5989 0.0260 0.8137 0.6299 -0.0016 0.0000 -0.0178 -0.1433 0.278 + 13 6.0123 3.7903 3.4706 2.3996 0.0138 0.7794 0.6360 -0.0053 0.0000 -0.0174 -0.1579 0.277 + 14 6.9353 3.6075 3.3775 2.2467 0.0136 0.7665 0.6254 -0.0032 0.0000 -0.0177 -0.1558 0.278 + 15 7.8737 3.4215 3.2389 2.1116 0.0117 0.7595 0.6197 -0.0026 0.0000 -0.0176 -0.1545 0.278 + 16 8.8172 3.2345 3.0619 1.9867 0.0106 0.7558 0.6168 -0.0025 0.0000 -0.0175 -0.1537 0.278 + 17 9.7556 3.0486 2.8543 1.8674 0.0106 0.7538 0.6151 -0.0026 0.0000 -0.0173 -0.1531 0.278 + 18 10.6786 2.8657 2.6239 1.7526 0.0114 0.7526 0.6141 -0.0027 0.0000 -0.0171 -0.1527 0.278 + 19 11.5760 2.6879 2.3787 1.6411 0.0128 0.7514 0.6131 -0.0028 0.0000 -0.0168 -0.1523 0.277 + 20 12.4328 2.5181 2.1010 1.5325 0.0148 0.7490 0.6112 -0.0030 0.0000 -0.0163 -0.1514 0.277 + 21 13.2400 2.3582 1.8520 1.4257 0.0175 0.7441 0.6072 -0.0031 0.0000 -0.0157 -0.1500 0.276 + 22 13.9941 2.2087 1.6074 1.3187 0.0213 0.7348 0.5996 -0.0031 0.0000 -0.0147 -0.1474 0.274 + 23 14.6868 2.0715 1.3716 1.2085 0.0266 0.7180 0.5859 -0.0028 0.0000 -0.0130 -0.1428 0.272 + 24 15.3105 1.9479 1.1479 1.0907 0.0334 0.6891 0.5623 -0.0024 0.0000 -0.0106 -0.1354 0.269 + 25 15.8583 1.8393 0.9381 0.9592 0.0412 0.6417 0.5236 -0.0013 0.0000 -0.0080 -0.1244 0.265 + 26 16.3244 1.7470 0.7427 0.8085 0.0490 0.5691 0.4644 0.0022 0.0000 -0.0086 -0.1118 0.269 + 27 16.6722 1.4928 0.4131 0.6454 0.0576 1.4633 0.4350 -0.0111 0.0000 -0.0097 -0.0575 0.272 + 28 16.9098 1.1466 0.2292 0.4793 0.0701 1.4193 0.4219 -0.0258 0.0000 0.0070 -0.0480 0.233 + 29 17.0696 0.9138 0.1104 0.2969 0.0806 1.1081 0.3294 -0.0370 0.0000 0.0237 -0.0290 0.178 + 30 17.1499 0.7967 0.0322 0.1007 0.0866 0.4350 0.1293 -0.0273 0.0000 0.0161 -0.0081 0.126 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.29266 Clsurf = 0.05607 - CYsurf = 0.01744 Cmsurf = -0.25972 - CDsurf = 0.00791 Cnsurf = 0.00304 - CDisurf = 0.00791 CDvsurf = 0.00000 + CLsurf = 0.29329 Clsurf = 0.05613 + CYsurf = 0.01729 Cmsurf = -0.26006 + CDsurf = 0.00766 Cnsurf = 0.00306 + CDisurf = 0.00766 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.57224 CDsurf = 0.01545 + CLsurf = 0.57344 CDsurf = 0.01496 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 3.8692 0.1377 0.6039 0.4675 0.3827 0.0000 -0.0250 0.1228 0.304 - 32 -0.1025 7.6885 1.0492 3.6117 0.1372 0.6003 0.4647 0.0783 0.0000 -0.0252 0.1170 0.304 - 33 -0.2837 7.5620 1.7073 3.5879 0.1358 0.6085 0.4711 0.0591 0.0000 -0.0233 0.1164 0.300 - 34 -0.5530 7.3741 2.3052 3.5700 0.1329 0.6218 0.4814 0.0527 0.0000 -0.0205 0.1161 0.293 - 35 -0.9075 7.1267 2.8223 3.5377 0.1278 0.6384 0.4942 0.0466 0.0000 -0.0175 0.1162 0.285 - 36 -1.3432 6.8226 3.2414 3.4854 0.1180 0.6579 0.5093 0.0404 0.0000 -0.0149 0.1170 0.279 - 37 -1.8554 6.4651 3.5491 3.4125 0.1004 0.6803 0.5266 0.0368 0.0000 -0.0127 0.1188 0.274 - 38 -2.4386 6.0582 3.7368 3.2950 0.0822 0.7020 0.5434 0.0289 0.0000 -0.0119 0.1214 0.272 - 39 -3.0862 5.6062 3.8005 3.1487 0.0699 0.7258 0.5619 0.0220 0.0000 -0.0120 0.1251 0.271 - 40 -3.7613 5.1351 3.4440 2.9768 0.0585 0.7501 0.5807 0.0140 0.0000 -0.0134 0.1299 0.273 - 41 -4.4532 4.6522 3.3149 2.7960 0.0456 0.7785 0.6026 0.0076 0.0000 -0.0158 0.1363 0.276 - 42 -5.1831 4.1429 3.0930 2.5920 0.0266 0.8115 0.6282 -0.0017 0.0000 -0.0190 0.1439 0.280 - 43 -6.0123 3.7903 3.4706 2.3972 0.0143 0.7786 0.6353 -0.0053 0.0000 -0.0188 0.1590 0.280 - 44 -6.9353 3.6075 3.3775 2.2448 0.0138 0.7658 0.6249 -0.0032 0.0000 -0.0192 0.1570 0.281 - 45 -7.8737 3.4215 3.2389 2.1100 0.0119 0.7589 0.6193 -0.0026 0.0000 -0.0192 0.1557 0.281 - 46 -8.8172 3.2345 3.0619 1.9851 0.0107 0.7552 0.6163 -0.0025 0.0000 -0.0190 0.1550 0.281 - 47 -9.7556 3.0486 2.8543 1.8661 0.0106 0.7533 0.6147 -0.0025 0.0000 -0.0188 0.1544 0.281 - 48 -10.6786 2.8657 2.6240 1.7515 0.0115 0.7521 0.6137 -0.0026 0.0000 -0.0186 0.1540 0.280 - 49 -11.5760 2.6879 2.3787 1.6402 0.0128 0.7510 0.6128 -0.0028 0.0000 -0.0183 0.1536 0.280 - 50 -12.4328 2.5181 2.1010 1.5317 0.0148 0.7486 0.6109 -0.0030 0.0000 -0.0179 0.1528 0.279 - 51 -13.2400 2.3582 1.8520 1.4251 0.0175 0.7437 0.6069 -0.0030 0.0000 -0.0173 0.1513 0.278 - 52 -13.9941 2.2087 1.6074 1.3182 0.0213 0.7345 0.5993 -0.0030 0.0000 -0.0163 0.1487 0.277 - 53 -14.6868 2.0715 1.3716 1.2081 0.0266 0.7177 0.5857 -0.0028 0.0000 -0.0146 0.1442 0.275 - 54 -15.3105 1.9479 1.1479 1.0906 0.0334 0.6890 0.5622 -0.0024 0.0000 -0.0122 0.1368 0.272 - 55 -15.8583 1.8393 0.9381 0.9592 0.0412 0.6417 0.5236 -0.0013 0.0000 -0.0095 0.1258 0.268 - 56 -16.3244 1.7470 0.7427 0.8089 0.0493 0.5694 0.4646 0.0022 0.0000 -0.0102 0.1132 0.272 - 57 -16.6722 1.4928 0.4131 0.6458 0.0579 1.4641 0.4352 -0.0109 0.0000 -0.0110 0.0581 0.275 - 58 -16.9098 1.1466 0.2292 0.4795 0.0702 1.4196 0.4220 -0.0256 0.0000 0.0061 0.0485 0.236 - 59 -17.0696 0.9138 0.1104 0.2969 0.0805 1.1080 0.3294 -0.0368 0.0000 0.0231 0.0292 0.180 - 60 -17.1499 0.7967 0.0322 0.1006 0.0859 0.4346 0.1292 -0.0270 0.0000 0.0159 0.0082 0.127 + 31 -0.0114 7.7520 0.3539 3.8862 0.1377 0.6067 0.4697 0.3830 0.0000 -0.0265 0.1244 0.306 + 32 -0.1025 7.6885 1.0491 3.6270 0.1373 0.6028 0.4667 0.0782 0.0000 -0.0265 0.1184 0.307 + 33 -0.2837 7.5620 1.7073 3.6032 0.1361 0.6112 0.4731 0.0591 0.0000 -0.0246 0.1179 0.302 + 34 -0.5530 7.3741 2.3052 3.5841 0.1335 0.6244 0.4834 0.0511 0.0000 -0.0218 0.1175 0.295 + 35 -0.9075 7.1267 2.8223 3.5537 0.1284 0.6412 0.4964 0.0470 0.0000 -0.0188 0.1177 0.288 + 36 -1.3432 6.8226 3.2414 3.5001 0.1186 0.6607 0.5115 0.0396 0.0000 -0.0161 0.1185 0.282 + 37 -1.8554 6.4651 3.5491 3.4176 0.1010 0.6821 0.5280 0.0297 0.0000 -0.0142 0.1201 0.277 + 38 -2.4386 6.0582 3.7368 3.3055 0.0828 0.7045 0.5454 0.0266 0.0000 -0.0130 0.1226 0.274 + 39 -3.0862 5.6062 3.8005 3.1609 0.0707 0.7287 0.5641 0.0214 0.0000 -0.0129 0.1263 0.273 + 40 -3.7613 5.1351 3.4440 2.9890 0.0591 0.7528 0.5828 0.0175 0.0000 -0.0139 0.1308 0.274 + 41 -4.4532 4.6522 3.3149 2.8078 0.0456 0.7818 0.6052 0.0070 0.0000 -0.0159 0.1369 0.276 + 42 -5.1831 4.1429 3.0930 2.5989 0.0260 0.8137 0.6299 -0.0016 0.0000 -0.0178 0.1433 0.278 + 43 -6.0123 3.7903 3.4706 2.3996 0.0138 0.7794 0.6360 -0.0053 0.0000 -0.0174 0.1579 0.277 + 44 -6.9353 3.6075 3.3775 2.2467 0.0136 0.7665 0.6254 -0.0032 0.0000 -0.0177 0.1558 0.278 + 45 -7.8737 3.4215 3.2389 2.1116 0.0117 0.7595 0.6197 -0.0026 0.0000 -0.0176 0.1545 0.278 + 46 -8.8172 3.2345 3.0619 1.9867 0.0106 0.7558 0.6168 -0.0025 0.0000 -0.0175 0.1537 0.278 + 47 -9.7556 3.0486 2.8543 1.8674 0.0106 0.7538 0.6151 -0.0026 0.0000 -0.0173 0.1531 0.278 + 48 -10.6786 2.8657 2.6239 1.7526 0.0114 0.7526 0.6141 -0.0027 0.0000 -0.0171 0.1527 0.278 + 49 -11.5760 2.6879 2.3787 1.6411 0.0128 0.7514 0.6131 -0.0028 0.0000 -0.0168 0.1523 0.277 + 50 -12.4328 2.5181 2.1010 1.5325 0.0148 0.7490 0.6112 -0.0030 0.0000 -0.0163 0.1514 0.277 + 51 -13.2400 2.3582 1.8520 1.4257 0.0175 0.7441 0.6072 -0.0031 0.0000 -0.0157 0.1500 0.276 + 52 -13.9941 2.2087 1.6074 1.3187 0.0213 0.7348 0.5996 -0.0031 0.0000 -0.0147 0.1474 0.274 + 53 -14.6868 2.0715 1.3716 1.2085 0.0266 0.7180 0.5859 -0.0028 0.0000 -0.0130 0.1428 0.272 + 54 -15.3105 1.9479 1.1479 1.0907 0.0334 0.6891 0.5623 -0.0024 0.0000 -0.0106 0.1354 0.269 + 55 -15.8583 1.8393 0.9381 0.9592 0.0412 0.6417 0.5236 -0.0013 0.0000 -0.0080 0.1244 0.265 + 56 -16.3244 1.7470 0.7427 0.8085 0.0490 0.5691 0.4644 0.0022 0.0000 -0.0086 0.1118 0.269 + 57 -16.6722 1.4928 0.4131 0.6454 0.0576 1.4633 0.4350 -0.0111 0.0000 -0.0097 0.0575 0.272 + 58 -16.9098 1.1466 0.2292 0.4793 0.0701 1.4193 0.4219 -0.0258 0.0000 0.0070 0.0480 0.233 + 59 -17.0696 0.9138 0.1104 0.2969 0.0806 1.1081 0.3294 -0.0370 0.0000 0.0237 0.0290 0.178 + 60 -17.1499 0.7967 0.0322 0.1007 0.0866 0.4350 0.1293 -0.0273 0.0000 0.0161 0.0081 0.126 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02623 Clsurf = -0.00281 - CYsurf = -0.00415 Cmsurf = -0.12828 - CDsurf = 0.00149 Cnsurf = 0.00236 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02610 Clsurf = -0.00280 + CYsurf = -0.00413 Cmsurf = -0.12766 + CDsurf = 0.00149 Cnsurf = 0.00235 CDisurf = 0.00149 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.15983 CDsurf = 0.00899 + CLsurf = 0.15903 CDsurf = 0.00895 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.5510 0.0896 0.1647 0.1262 0.0381 0.0000 -0.0073 -0.0339 0.308 - 62 0.0418 4.2566 0.2392 0.5089 0.0898 0.1554 0.1190 0.0110 0.0000 -0.0072 -0.0319 0.310 - 63 0.1156 4.2274 0.3930 0.5061 0.0898 0.1558 0.1194 0.0093 0.0000 -0.0068 -0.0316 0.307 - 64 0.2254 4.1839 0.5386 0.5053 0.0894 0.1573 0.1205 0.0089 0.0000 -0.0062 -0.0313 0.302 - 65 0.3698 4.1268 0.6730 0.5053 0.0884 0.1594 0.1221 0.0088 0.0000 -0.0054 -0.0310 0.295 - 66 0.5474 4.0565 0.7936 0.5051 0.0869 0.1622 0.1242 0.0088 0.0000 -0.0047 -0.0308 0.288 - 67 0.7617 3.9717 0.9441 0.5050 0.0846 0.1656 0.1269 0.0087 0.0000 -0.0039 -0.0308 0.281 - 68 1.0116 3.8728 1.0344 0.5048 0.0814 0.1698 0.1301 0.0087 0.0000 -0.0032 -0.0309 0.275 - 69 1.2891 3.7630 1.1046 0.5039 0.0775 0.1745 0.1337 0.0088 0.0000 -0.0026 -0.0312 0.270 - 70 1.5912 3.6435 1.1542 0.5033 0.0731 0.1800 0.1379 0.0088 0.0000 -0.0022 -0.0317 0.266 - 71 1.9146 3.5155 1.1831 0.5026 0.0687 0.1863 0.1427 0.0089 0.0000 -0.0018 -0.0324 0.262 - 72 2.2558 3.3805 1.1921 0.5017 0.0648 0.1934 0.1482 0.0091 0.0000 -0.0014 -0.0333 0.260 - 73 2.6109 3.2400 1.1821 0.5009 0.0615 0.2015 0.1544 0.0092 0.0000 -0.0011 -0.0344 0.257 - 74 2.9762 3.0955 1.1548 0.4998 0.0589 0.2105 0.1613 0.0094 0.0000 -0.0008 -0.0356 0.255 - 75 3.3476 2.9485 1.1122 0.4982 0.0570 0.2203 0.1688 0.0095 0.0000 -0.0005 -0.0369 0.253 - 76 3.7210 2.8008 1.0564 0.4955 0.0556 0.2307 0.1767 0.0096 0.0000 -0.0001 -0.0383 0.250 - 77 4.0924 2.6538 0.9900 0.4911 0.0546 0.2414 0.1849 0.0097 0.0000 0.0003 -0.0397 0.248 - 78 4.4577 2.5093 0.9155 0.4845 0.0541 0.2519 0.1930 0.0097 0.0000 0.0009 -0.0410 0.246 - 79 4.8128 2.3687 0.8353 0.4749 0.0540 0.2616 0.2004 0.0096 0.0000 0.0015 -0.0421 0.243 - 80 5.1540 2.2338 0.7518 0.4619 0.0543 0.2699 0.2067 0.0095 0.0000 0.0022 -0.0428 0.239 - 81 5.4774 2.1058 0.6671 0.4452 0.0552 0.2760 0.2114 0.0093 0.0000 0.0032 -0.0430 0.235 - 82 5.7795 1.9862 0.5830 0.4238 0.0565 0.2786 0.2134 0.0089 0.0000 0.0044 -0.0424 0.229 - 83 6.0570 1.8764 0.5012 0.3978 0.0583 0.2769 0.2121 0.0084 0.0000 0.0059 -0.0409 0.222 - 84 6.3069 1.7776 0.4225 0.3665 0.0603 0.2693 0.2063 0.0077 0.0000 0.0077 -0.0381 0.213 - 85 6.5264 1.6907 0.3478 0.3300 0.0625 0.2550 0.1953 0.0069 0.0000 0.0096 -0.0341 0.201 - 86 6.7314 1.6096 0.3326 0.2858 0.0647 0.2321 0.1777 0.0058 0.0000 0.0115 -0.0288 0.185 - 87 6.9144 1.5372 0.2507 0.2314 0.0669 0.1968 0.1507 0.0044 0.0000 0.0126 -0.0220 0.166 - 88 7.0535 1.4822 0.1746 0.1703 0.0686 0.1502 0.1151 0.0029 0.0000 0.0120 -0.0148 0.146 - 89 7.1471 1.4451 0.1029 0.1042 0.0698 0.0944 0.0723 0.0013 0.0000 0.0089 -0.0082 0.127 + 61 0.0047 4.2713 0.0803 0.5464 0.0897 0.1633 0.1251 0.0376 0.0000 -0.0073 -0.0337 0.308 + 62 0.0418 4.2566 0.2392 0.5050 0.0899 0.1542 0.1181 0.0110 0.0000 -0.0072 -0.0316 0.311 + 63 0.1156 4.2274 0.3930 0.5020 0.0899 0.1546 0.1184 0.0093 0.0000 -0.0068 -0.0314 0.307 + 64 0.2254 4.1839 0.5386 0.5013 0.0895 0.1560 0.1195 0.0089 0.0000 -0.0062 -0.0311 0.302 + 65 0.3698 4.1268 0.6730 0.5015 0.0885 0.1582 0.1212 0.0087 0.0000 -0.0054 -0.0308 0.295 + 66 0.5474 4.0565 0.7936 0.5014 0.0870 0.1610 0.1233 0.0087 0.0000 -0.0046 -0.0306 0.288 + 67 0.7617 3.9717 0.9441 0.5013 0.0847 0.1644 0.1259 0.0087 0.0000 -0.0039 -0.0305 0.281 + 68 1.0116 3.8728 1.0344 0.5007 0.0815 0.1684 0.1290 0.0086 0.0000 -0.0032 -0.0306 0.275 + 69 1.2891 3.7630 1.1046 0.5003 0.0776 0.1732 0.1327 0.0087 0.0000 -0.0026 -0.0310 0.270 + 70 1.5912 3.6435 1.1542 0.4997 0.0733 0.1787 0.1369 0.0088 0.0000 -0.0022 -0.0315 0.266 + 71 1.9146 3.5155 1.1831 0.4990 0.0689 0.1850 0.1417 0.0089 0.0000 -0.0018 -0.0322 0.263 + 72 2.2558 3.3805 1.1921 0.4984 0.0649 0.1922 0.1472 0.0090 0.0000 -0.0014 -0.0331 0.260 + 73 2.6109 3.2400 1.1821 0.4978 0.0616 0.2003 0.1534 0.0092 0.0000 -0.0011 -0.0342 0.257 + 74 2.9762 3.0955 1.1548 0.4971 0.0591 0.2094 0.1604 0.0094 0.0000 -0.0008 -0.0354 0.255 + 75 3.3476 2.9485 1.1122 0.4957 0.0571 0.2192 0.1679 0.0095 0.0000 -0.0005 -0.0367 0.253 + 76 3.7210 2.8008 1.0564 0.4932 0.0557 0.2297 0.1759 0.0096 0.0000 -0.0001 -0.0382 0.251 + 77 4.0924 2.6538 0.9900 0.4891 0.0547 0.2404 0.1841 0.0097 0.0000 0.0003 -0.0396 0.248 + 78 4.4577 2.5093 0.9155 0.4828 0.0541 0.2510 0.1923 0.0097 0.0000 0.0008 -0.0409 0.246 + 79 4.8128 2.3687 0.8353 0.4735 0.0540 0.2609 0.1998 0.0096 0.0000 0.0015 -0.0420 0.243 + 80 5.1540 2.2338 0.7518 0.4608 0.0544 0.2692 0.2062 0.0095 0.0000 0.0022 -0.0427 0.239 + 81 5.4774 2.1058 0.6671 0.4441 0.0552 0.2753 0.2109 0.0093 0.0000 0.0032 -0.0429 0.235 + 82 5.7795 1.9862 0.5830 0.4230 0.0566 0.2780 0.2130 0.0088 0.0000 0.0044 -0.0423 0.229 + 83 6.0570 1.8764 0.5012 0.3971 0.0583 0.2764 0.2117 0.0084 0.0000 0.0059 -0.0408 0.222 + 84 6.3069 1.7776 0.4225 0.3660 0.0603 0.2690 0.2060 0.0077 0.0000 0.0077 -0.0381 0.213 + 85 6.5264 1.6907 0.3478 0.3296 0.0625 0.2547 0.1951 0.0068 0.0000 0.0096 -0.0341 0.201 + 86 6.7314 1.6096 0.3326 0.2856 0.0647 0.2318 0.1776 0.0058 0.0000 0.0115 -0.0288 0.185 + 87 6.9144 1.5372 0.2507 0.2311 0.0669 0.1966 0.1505 0.0044 0.0000 0.0126 -0.0219 0.166 + 88 7.0535 1.4822 0.1746 0.1701 0.0686 0.1501 0.1150 0.0029 0.0000 0.0120 -0.0148 0.146 + 89 7.1471 1.4451 0.1029 0.1042 0.0698 0.0943 0.0722 0.0013 0.0000 0.0089 -0.0082 0.127 90 7.1941 1.4265 0.0340 0.0351 0.0705 0.0323 0.0247 -0.0002 0.0000 0.0033 -0.0026 0.117 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02623 Clsurf = 0.00281 - CYsurf = 0.00415 Cmsurf = -0.12828 - CDsurf = 0.00149 Cnsurf = -0.00236 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02610 Clsurf = 0.00280 + CYsurf = 0.00413 Cmsurf = -0.12766 + CDsurf = 0.00149 Cnsurf = -0.00235 CDisurf = 0.00149 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.15982 CDsurf = 0.00899 + CLsurf = 0.15903 CDsurf = 0.00895 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.5510 0.0896 0.1647 0.1262 0.0381 0.0000 -0.0073 0.0339 0.308 - 92 -0.0418 4.2566 0.2392 0.5089 0.0898 0.1554 0.1190 0.0110 0.0000 -0.0072 0.0319 0.310 - 93 -0.1156 4.2274 0.3930 0.5061 0.0898 0.1558 0.1194 0.0093 0.0000 -0.0068 0.0316 0.307 - 94 -0.2254 4.1839 0.5386 0.5053 0.0894 0.1573 0.1205 0.0089 0.0000 -0.0062 0.0313 0.302 - 95 -0.3698 4.1268 0.6730 0.5053 0.0884 0.1594 0.1221 0.0088 0.0000 -0.0054 0.0310 0.295 - 96 -0.5474 4.0565 0.7936 0.5051 0.0869 0.1622 0.1242 0.0088 0.0000 -0.0047 0.0308 0.288 - 97 -0.7617 3.9717 0.9441 0.5050 0.0846 0.1656 0.1269 0.0087 0.0000 -0.0039 0.0308 0.281 - 98 -1.0116 3.8728 1.0344 0.5048 0.0814 0.1698 0.1301 0.0087 0.0000 -0.0032 0.0309 0.275 - 99 -1.2891 3.7630 1.1046 0.5039 0.0775 0.1745 0.1337 0.0088 0.0000 -0.0026 0.0312 0.270 - 100 -1.5912 3.6435 1.1542 0.5033 0.0731 0.1800 0.1379 0.0088 0.0000 -0.0022 0.0317 0.266 - 101 -1.9146 3.5155 1.1831 0.5026 0.0687 0.1863 0.1427 0.0089 0.0000 -0.0018 0.0324 0.262 - 102 -2.2558 3.3805 1.1921 0.5017 0.0648 0.1934 0.1482 0.0091 0.0000 -0.0014 0.0333 0.260 - 103 -2.6109 3.2400 1.1821 0.5009 0.0615 0.2015 0.1544 0.0092 0.0000 -0.0011 0.0344 0.257 - 104 -2.9762 3.0955 1.1548 0.4998 0.0589 0.2105 0.1613 0.0094 0.0000 -0.0008 0.0356 0.255 - 105 -3.3476 2.9485 1.1122 0.4982 0.0570 0.2203 0.1688 0.0095 0.0000 -0.0005 0.0369 0.253 - 106 -3.7210 2.8008 1.0564 0.4955 0.0556 0.2307 0.1767 0.0096 0.0000 -0.0001 0.0383 0.250 - 107 -4.0924 2.6538 0.9900 0.4911 0.0546 0.2414 0.1849 0.0097 0.0000 0.0003 0.0397 0.248 - 108 -4.4577 2.5093 0.9155 0.4845 0.0541 0.2519 0.1930 0.0097 0.0000 0.0009 0.0410 0.246 - 109 -4.8128 2.3687 0.8353 0.4749 0.0540 0.2616 0.2004 0.0096 0.0000 0.0015 0.0421 0.243 - 110 -5.1540 2.2338 0.7518 0.4619 0.0543 0.2699 0.2067 0.0095 0.0000 0.0022 0.0428 0.239 - 111 -5.4774 2.1058 0.6671 0.4451 0.0552 0.2760 0.2114 0.0093 0.0000 0.0032 0.0430 0.235 - 112 -5.7795 1.9862 0.5830 0.4238 0.0565 0.2786 0.2134 0.0089 0.0000 0.0044 0.0424 0.229 - 113 -6.0570 1.8764 0.5012 0.3978 0.0583 0.2769 0.2121 0.0084 0.0000 0.0059 0.0409 0.222 - 114 -6.3069 1.7776 0.4225 0.3665 0.0603 0.2693 0.2063 0.0077 0.0000 0.0077 0.0381 0.213 - 115 -6.5264 1.6907 0.3478 0.3300 0.0625 0.2550 0.1953 0.0069 0.0000 0.0096 0.0341 0.201 - 116 -6.7314 1.6096 0.3326 0.2858 0.0647 0.2321 0.1777 0.0058 0.0000 0.0115 0.0288 0.185 - 117 -6.9144 1.5372 0.2507 0.2314 0.0669 0.1968 0.1507 0.0044 0.0000 0.0126 0.0220 0.166 - 118 -7.0535 1.4822 0.1746 0.1703 0.0686 0.1502 0.1151 0.0029 0.0000 0.0120 0.0148 0.146 - 119 -7.1471 1.4451 0.1029 0.1042 0.0698 0.0944 0.0723 0.0013 0.0000 0.0089 0.0082 0.127 + 91 -0.0047 4.2713 0.0803 0.5464 0.0897 0.1633 0.1251 0.0376 0.0000 -0.0073 0.0337 0.308 + 92 -0.0418 4.2566 0.2392 0.5050 0.0899 0.1542 0.1181 0.0110 0.0000 -0.0072 0.0316 0.311 + 93 -0.1156 4.2274 0.3930 0.5020 0.0899 0.1546 0.1184 0.0093 0.0000 -0.0068 0.0314 0.307 + 94 -0.2254 4.1839 0.5386 0.5013 0.0895 0.1560 0.1195 0.0089 0.0000 -0.0062 0.0311 0.302 + 95 -0.3698 4.1268 0.6730 0.5015 0.0885 0.1582 0.1212 0.0087 0.0000 -0.0054 0.0308 0.295 + 96 -0.5474 4.0565 0.7936 0.5014 0.0870 0.1610 0.1233 0.0087 0.0000 -0.0046 0.0306 0.288 + 97 -0.7617 3.9717 0.9441 0.5013 0.0847 0.1644 0.1259 0.0087 0.0000 -0.0039 0.0305 0.281 + 98 -1.0116 3.8728 1.0344 0.5007 0.0815 0.1684 0.1290 0.0086 0.0000 -0.0032 0.0306 0.275 + 99 -1.2891 3.7630 1.1046 0.5003 0.0776 0.1732 0.1327 0.0087 0.0000 -0.0026 0.0310 0.270 + 100 -1.5912 3.6435 1.1542 0.4997 0.0733 0.1787 0.1369 0.0088 0.0000 -0.0022 0.0315 0.266 + 101 -1.9146 3.5155 1.1831 0.4990 0.0689 0.1850 0.1417 0.0089 0.0000 -0.0018 0.0322 0.263 + 102 -2.2558 3.3805 1.1921 0.4984 0.0649 0.1922 0.1472 0.0090 0.0000 -0.0014 0.0331 0.260 + 103 -2.6109 3.2400 1.1821 0.4978 0.0616 0.2003 0.1534 0.0092 0.0000 -0.0011 0.0342 0.257 + 104 -2.9762 3.0955 1.1548 0.4971 0.0591 0.2094 0.1604 0.0094 0.0000 -0.0008 0.0354 0.255 + 105 -3.3476 2.9485 1.1122 0.4957 0.0571 0.2192 0.1679 0.0095 0.0000 -0.0005 0.0367 0.253 + 106 -3.7210 2.8008 1.0564 0.4932 0.0557 0.2297 0.1759 0.0096 0.0000 -0.0001 0.0382 0.251 + 107 -4.0924 2.6538 0.9900 0.4891 0.0547 0.2404 0.1841 0.0097 0.0000 0.0003 0.0396 0.248 + 108 -4.4577 2.5093 0.9155 0.4828 0.0541 0.2510 0.1923 0.0097 0.0000 0.0008 0.0409 0.246 + 109 -4.8128 2.3687 0.8353 0.4735 0.0540 0.2609 0.1998 0.0096 0.0000 0.0015 0.0420 0.243 + 110 -5.1540 2.2338 0.7518 0.4608 0.0544 0.2692 0.2062 0.0095 0.0000 0.0022 0.0427 0.239 + 111 -5.4774 2.1058 0.6671 0.4441 0.0552 0.2753 0.2109 0.0093 0.0000 0.0032 0.0429 0.235 + 112 -5.7795 1.9862 0.5830 0.4230 0.0566 0.2780 0.2130 0.0088 0.0000 0.0044 0.0423 0.229 + 113 -6.0570 1.8764 0.5012 0.3971 0.0583 0.2764 0.2117 0.0084 0.0000 0.0059 0.0408 0.222 + 114 -6.3069 1.7776 0.4225 0.3660 0.0603 0.2690 0.2060 0.0077 0.0000 0.0077 0.0381 0.213 + 115 -6.5264 1.6907 0.3478 0.3296 0.0625 0.2547 0.1951 0.0068 0.0000 0.0096 0.0341 0.201 + 116 -6.7314 1.6096 0.3326 0.2856 0.0647 0.2318 0.1776 0.0058 0.0000 0.0115 0.0288 0.185 + 117 -6.9144 1.5372 0.2507 0.2311 0.0669 0.1966 0.1505 0.0044 0.0000 0.0126 0.0219 0.166 + 118 -7.0535 1.4822 0.1746 0.1701 0.0686 0.1501 0.1150 0.0029 0.0000 0.0120 0.0148 0.146 + 119 -7.1471 1.4451 0.1029 0.1042 0.0698 0.0943 0.0722 0.0013 0.0000 0.0089 0.0082 0.127 120 -7.1941 1.4265 0.0340 0.0351 0.0705 0.0323 0.0247 -0.0002 0.0000 0.0033 0.0026 0.117 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.333 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.340 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.350 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.361 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.365 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.368 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.366 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.356 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.335 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.301 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.265 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.261 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.258 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.255 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.242 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.214 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.201 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.187 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.168 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.147 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.132 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 + 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.311 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.319 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.312 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.326 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.325 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.326 + 127 0.0000 7.4000 2.2957 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.331 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.319 + 129 0.0000 5.8609 2.1733 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.306 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.276 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.199 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.182 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.164 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.142 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.123 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00641 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.04697 + CLsurf = 0.00634 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = 0.04704 CDsurf = -0.00023 Cnsurf = -0.00000 CDisurf = -0.00023 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00646 CDsurf = -0.00023 + CLsurf = 0.00639 CDsurf = -0.00024 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.1407 0.1259 0.0634 0.0055 -0.0018 0.0000 0.0037 0.0003 -0.420 - 152 -1.3090 31.2096 11.6724 0.2043 0.1368 0.0253 0.0066 -0.0007 0.0000 0.0044 0.0007 -0.421 - 153 -0.9350 34.0626 12.7394 0.2276 0.1305 0.0163 0.0067 -0.0002 0.0000 0.0052 0.0012 -0.517 - 154 -0.5610 36.1619 13.5246 0.2409 0.1292 0.0111 0.0067 0.0002 0.0000 0.0055 0.0017 -0.572 - 155 -0.1870 37.5332 14.0374 0.2484 0.1302 0.0076 0.0066 0.0008 0.0000 0.0056 0.0027 -0.595 - 156 0.1870 37.5332 14.0374 0.2484 0.1302 0.0076 0.0066 0.0008 0.0000 0.0056 0.0027 -0.595 - 157 0.5610 36.1619 13.5246 0.2409 0.1292 0.0111 0.0067 0.0002 0.0000 0.0055 0.0017 -0.572 - 158 0.9350 34.0626 12.7394 0.2275 0.1305 0.0163 0.0067 -0.0002 0.0000 0.0052 0.0012 -0.517 - 159 1.3090 31.2096 11.6724 0.2043 0.1368 0.0253 0.0066 -0.0007 0.0000 0.0044 0.0007 -0.421 - 160 1.6830 26.5957 9.9468 0.1407 0.1259 0.0634 0.0055 -0.0018 0.0000 0.0037 0.0003 -0.420 + 151 -1.6830 26.5957 9.9468 0.1390 0.1258 0.0627 0.0054 -0.0019 0.0000 0.0037 0.0003 -0.433 + 152 -1.3090 31.2096 11.6724 0.2019 0.1369 0.0250 0.0066 -0.0007 0.0000 0.0045 0.0007 -0.432 + 153 -0.9350 34.0626 12.7394 0.2251 0.1307 0.0161 0.0066 -0.0002 0.0000 0.0052 0.0012 -0.528 + 154 -0.5610 36.1619 13.5246 0.2384 0.1294 0.0110 0.0066 0.0002 0.0000 0.0055 0.0017 -0.584 + 155 -0.1870 37.5332 14.0374 0.2459 0.1304 0.0076 0.0065 0.0008 0.0000 0.0056 0.0027 -0.606 + 156 0.1870 37.5332 14.0374 0.2459 0.1304 0.0076 0.0065 0.0008 0.0000 0.0056 0.0027 -0.606 + 157 0.5610 36.1619 13.5246 0.2384 0.1294 0.0110 0.0066 0.0002 0.0000 0.0055 0.0017 -0.584 + 158 0.9350 34.0626 12.7394 0.2251 0.1307 0.0161 0.0066 -0.0002 0.0000 0.0052 0.0012 -0.528 + 159 1.3090 31.2096 11.6724 0.2019 0.1369 0.0250 0.0066 -0.0007 0.0000 0.0045 0.0007 -0.432 + 160 1.6830 26.5957 9.9468 0.1390 0.1258 0.0627 0.0054 -0.0019 0.0000 0.0037 0.0003 -0.433 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.684 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.317 - 163 0.0000 34.0626 12.7394 -0.0000 0.0001 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.028 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.112 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 - 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.449 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.502 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.552 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.604 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.687 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 1.786 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.119 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.183 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.257 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.325 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.500 + 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.560 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.592 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.630 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.697 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_01_05.txt b/regression/scripts/AVL/avl_files/strip_forces_case_01_05.txt index e50125e578..6cf6585826 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_01_05.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_01_05.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.37282 Clsurf = -0.07238 - CYsurf = -0.02021 Cmsurf = -0.33364 - CDsurf = 0.01240 Cnsurf = -0.00686 - CDisurf = 0.01240 CDvsurf = 0.00000 + CLsurf = 0.37347 Clsurf = -0.07245 + CYsurf = -0.01996 Cmsurf = -0.33399 + CDsurf = 0.01201 Cnsurf = -0.00688 + CDisurf = 0.01201 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.72870 CDsurf = 0.02420 + CLsurf = 0.72994 CDsurf = 0.02344 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 4.8171 0.1732 0.7173 0.5555 0.5731 0.0000 -0.0308 -0.1529 0.305 - 2 0.1025 7.6885 1.0492 4.4294 0.1728 0.7311 0.5662 0.1153 0.0000 -0.0311 -0.1439 0.305 - 3 0.2837 7.5620 1.7073 4.3955 0.1715 0.7423 0.5750 0.0867 0.0000 -0.0288 -0.1431 0.300 - 4 0.5530 7.3741 2.3052 4.3747 0.1685 0.7594 0.5882 0.0774 0.0000 -0.0252 -0.1427 0.293 - 5 0.9075 7.1267 2.8223 4.3386 0.1626 0.7810 0.6049 0.0688 0.0000 -0.0215 -0.1428 0.285 - 6 1.3432 6.8226 3.2414 4.2816 0.1498 0.8068 0.6249 0.0600 0.0000 -0.0181 -0.1440 0.279 - 7 1.8554 6.4651 3.5491 4.2045 0.1244 0.8372 0.6484 0.0553 0.0000 -0.0152 -0.1464 0.273 - 8 2.4386 6.0582 3.7368 4.0734 0.0989 0.8676 0.6720 0.0442 0.0000 -0.0139 -0.1499 0.271 - 9 3.0862 5.6062 3.8005 3.9119 0.0853 0.9022 0.6988 0.0346 0.0000 -0.0137 -0.1549 0.270 - 10 3.7613 5.1351 3.4440 3.7202 0.0734 0.9387 0.7270 0.0234 0.0000 -0.0148 -0.1613 0.270 - 11 4.4532 4.6522 3.3149 3.5197 0.0593 0.9819 0.7605 0.0144 0.0000 -0.0170 -0.1697 0.272 - 12 5.1831 4.1429 3.0930 3.2889 0.0378 1.0326 0.7997 0.0007 0.0000 -0.0197 -0.1796 0.275 - 13 6.0123 3.7903 3.4706 3.0633 0.0234 1.0001 0.8148 -0.0046 0.0000 -0.0179 -0.1986 0.272 - 14 6.9353 3.6075 3.3775 2.8844 0.0216 0.9891 0.8058 -0.0022 0.0000 -0.0182 -0.1969 0.273 - 15 7.8737 3.4215 3.2389 2.7235 0.0181 0.9846 0.8022 -0.0018 0.0000 -0.0181 -0.1960 0.273 - 16 8.8172 3.2345 3.0619 2.5718 0.0159 0.9835 0.8013 -0.0020 0.0000 -0.0179 -0.1957 0.272 - 17 9.7556 3.0486 2.8543 2.4249 0.0155 0.9840 0.8017 -0.0024 0.0000 -0.0177 -0.1956 0.272 - 18 10.6786 2.8657 2.6240 2.2815 0.0164 0.9849 0.8025 -0.0029 0.0000 -0.0174 -0.1955 0.272 - 19 11.5760 2.6879 2.3787 2.1408 0.0182 0.9854 0.8029 -0.0034 0.0000 -0.0170 -0.1952 0.271 - 20 12.4328 2.5181 2.1010 2.0025 0.0207 0.9840 0.8017 -0.0038 0.0000 -0.0165 -0.1944 0.271 - 21 13.2400 2.3582 1.8520 1.8654 0.0242 0.9788 0.7975 -0.0041 0.0000 -0.0156 -0.1928 0.270 - 22 13.9941 2.2087 1.6074 1.7271 0.0292 0.9676 0.7883 -0.0042 0.0000 -0.0143 -0.1895 0.268 - 23 14.6868 2.0715 1.3716 1.5840 0.0361 0.9462 0.7709 -0.0040 0.0000 -0.0121 -0.1837 0.266 - 24 15.3105 1.9479 1.1479 1.4304 0.0450 0.9086 0.7402 -0.0034 0.0000 -0.0090 -0.1741 0.262 - 25 15.8583 1.8393 0.9381 1.2580 0.0552 0.8460 0.6893 -0.0016 0.0000 -0.0056 -0.1597 0.258 - 26 16.3244 1.7470 0.7427 1.0604 0.0655 0.7499 0.6110 0.0045 0.0000 -0.0070 -0.1435 0.261 - 27 16.6722 1.4928 0.4131 0.8457 0.0765 1.9150 0.5732 -0.0192 0.0000 -0.0090 -0.0749 0.266 - 28 16.9098 1.1466 0.2292 0.6272 0.0919 1.8597 0.5567 -0.0448 0.0000 0.0131 -0.0624 0.227 - 29 17.0696 0.9138 0.1104 0.3878 0.1046 1.4556 0.4357 -0.0645 0.0000 0.0344 -0.0373 0.171 - 30 17.1499 0.7967 0.0322 0.1314 0.1112 0.5753 0.1722 -0.0483 0.0000 0.0226 -0.0103 0.119 + 1 0.0114 7.7520 0.3539 4.8343 0.1732 0.7201 0.5577 0.5736 0.0000 -0.0323 -0.1545 0.308 + 2 0.1025 7.6885 1.0491 4.4446 0.1729 0.7337 0.5682 0.1153 0.0000 -0.0323 -0.1453 0.307 + 3 0.2837 7.5620 1.7073 4.4108 0.1718 0.7450 0.5770 0.0868 0.0000 -0.0300 -0.1446 0.302 + 4 0.5530 7.3741 2.3052 4.3880 0.1690 0.7621 0.5903 0.0750 0.0000 -0.0265 -0.1441 0.295 + 5 0.9075 7.1267 2.8223 4.3547 0.1632 0.7838 0.6071 0.0694 0.0000 -0.0227 -0.1443 0.287 + 6 1.3432 6.8226 3.2414 4.2958 0.1504 0.8097 0.6271 0.0588 0.0000 -0.0193 -0.1454 0.281 + 7 1.8554 6.4651 3.5491 4.2047 0.1250 0.8389 0.6498 0.0446 0.0000 -0.0168 -0.1476 0.276 + 8 2.4386 6.0582 3.7368 4.0820 0.0996 0.8700 0.6739 0.0407 0.0000 -0.0151 -0.1511 0.272 + 9 3.0862 5.6062 3.8005 3.9236 0.0861 0.9051 0.7010 0.0336 0.0000 -0.0146 -0.1560 0.271 + 10 3.7613 5.1351 3.4440 3.7332 0.0740 0.9412 0.7289 0.0285 0.0000 -0.0153 -0.1622 0.271 + 11 4.4532 4.6522 3.3149 3.5340 0.0593 0.9861 0.7637 0.0134 0.0000 -0.0173 -0.1705 0.273 + 12 5.1831 4.1429 3.0930 3.2975 0.0372 1.0353 0.8018 0.0009 0.0000 -0.0184 -0.1790 0.273 + 13 6.0123 3.7903 3.4706 3.0657 0.0229 1.0009 0.8155 -0.0046 0.0000 -0.0165 -0.1975 0.270 + 14 6.9353 3.6075 3.3775 2.8862 0.0214 0.9897 0.8063 -0.0022 0.0000 -0.0167 -0.1957 0.271 + 15 7.8737 3.4215 3.2389 2.7250 0.0180 0.9851 0.8026 -0.0018 0.0000 -0.0166 -0.1948 0.271 + 16 8.8172 3.2345 3.0619 2.5735 0.0158 0.9842 0.8019 -0.0020 0.0000 -0.0163 -0.1944 0.270 + 17 9.7556 3.0486 2.8543 2.4262 0.0154 0.9845 0.8021 -0.0025 0.0000 -0.0161 -0.1943 0.270 + 18 10.6786 2.8657 2.6239 2.2826 0.0164 0.9854 0.8029 -0.0029 0.0000 -0.0158 -0.1942 0.270 + 19 11.5760 2.6879 2.3787 2.1417 0.0181 0.9858 0.8032 -0.0034 0.0000 -0.0155 -0.1939 0.269 + 20 12.4328 2.5181 2.1010 2.0032 0.0206 0.9843 0.8020 -0.0039 0.0000 -0.0149 -0.1931 0.269 + 21 13.2400 2.3582 1.8520 1.8660 0.0242 0.9791 0.7978 -0.0042 0.0000 -0.0141 -0.1914 0.268 + 22 13.9941 2.2087 1.6074 1.7277 0.0292 0.9679 0.7886 -0.0043 0.0000 -0.0127 -0.1882 0.266 + 23 14.6868 2.0715 1.3716 1.5844 0.0361 0.9464 0.7711 -0.0041 0.0000 -0.0106 -0.1824 0.264 + 24 15.3105 1.9479 1.1479 1.4305 0.0450 0.9086 0.7403 -0.0034 0.0000 -0.0074 -0.1727 0.260 + 25 15.8583 1.8393 0.9381 1.2580 0.0551 0.8460 0.6893 -0.0017 0.0000 -0.0041 -0.1583 0.256 + 26 16.3244 1.7470 0.7427 1.0600 0.0653 0.7496 0.6108 0.0044 0.0000 -0.0055 -0.1421 0.259 + 27 16.6722 1.4928 0.4131 0.8453 0.0762 1.9141 0.5730 -0.0194 0.0000 -0.0078 -0.0742 0.264 + 28 16.9098 1.1466 0.2292 0.6270 0.0919 1.8594 0.5566 -0.0450 0.0000 0.0140 -0.0619 0.225 + 29 17.0696 0.9138 0.1104 0.3878 0.1047 1.4558 0.4358 -0.0648 0.0000 0.0350 -0.0371 0.170 + 30 17.1499 0.7967 0.0322 0.1315 0.1119 0.5757 0.1723 -0.0487 0.0000 0.0228 -0.0102 0.118 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.37282 Clsurf = 0.07238 - CYsurf = 0.02021 Cmsurf = -0.33364 - CDsurf = 0.01240 Cnsurf = 0.00686 - CDisurf = 0.01240 CDvsurf = 0.00000 + CLsurf = 0.37347 Clsurf = 0.07245 + CYsurf = 0.01996 Cmsurf = -0.33399 + CDsurf = 0.01201 Cnsurf = 0.00688 + CDisurf = 0.01201 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.72870 CDsurf = 0.02420 + CLsurf = 0.72994 CDsurf = 0.02344 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 4.8171 0.1733 0.7173 0.5555 0.5731 0.0000 -0.0308 0.1529 0.305 - 32 -0.1025 7.6885 1.0492 4.4294 0.1728 0.7311 0.5662 0.1153 0.0000 -0.0311 0.1439 0.305 - 33 -0.2837 7.5620 1.7073 4.3955 0.1715 0.7423 0.5750 0.0867 0.0000 -0.0288 0.1431 0.300 - 34 -0.5530 7.3741 2.3052 4.3747 0.1685 0.7594 0.5882 0.0774 0.0000 -0.0252 0.1427 0.293 - 35 -0.9075 7.1267 2.8223 4.3386 0.1626 0.7810 0.6049 0.0688 0.0000 -0.0215 0.1428 0.285 - 36 -1.3432 6.8226 3.2414 4.2816 0.1498 0.8068 0.6249 0.0600 0.0000 -0.0181 0.1440 0.279 - 37 -1.8554 6.4651 3.5491 4.2045 0.1244 0.8372 0.6484 0.0553 0.0000 -0.0152 0.1464 0.273 - 38 -2.4386 6.0582 3.7368 4.0734 0.0989 0.8676 0.6720 0.0442 0.0000 -0.0139 0.1499 0.271 - 39 -3.0862 5.6062 3.8005 3.9119 0.0853 0.9022 0.6988 0.0346 0.0000 -0.0137 0.1549 0.270 - 40 -3.7613 5.1351 3.4440 3.7202 0.0734 0.9387 0.7270 0.0234 0.0000 -0.0148 0.1613 0.270 - 41 -4.4532 4.6522 3.3149 3.5197 0.0593 0.9819 0.7605 0.0144 0.0000 -0.0170 0.1697 0.272 - 42 -5.1831 4.1429 3.0930 3.2889 0.0378 1.0326 0.7997 0.0007 0.0000 -0.0197 0.1796 0.275 - 43 -6.0123 3.7903 3.4706 3.0632 0.0234 1.0001 0.8148 -0.0046 0.0000 -0.0179 0.1986 0.272 - 44 -6.9353 3.6075 3.3775 2.8844 0.0216 0.9891 0.8058 -0.0022 0.0000 -0.0182 0.1969 0.273 - 45 -7.8737 3.4215 3.2389 2.7235 0.0181 0.9846 0.8022 -0.0018 0.0000 -0.0181 0.1960 0.273 - 46 -8.8172 3.2345 3.0619 2.5718 0.0159 0.9835 0.8013 -0.0020 0.0000 -0.0179 0.1957 0.272 - 47 -9.7556 3.0486 2.8543 2.4249 0.0155 0.9840 0.8017 -0.0024 0.0000 -0.0177 0.1956 0.272 - 48 -10.6786 2.8657 2.6240 2.2815 0.0164 0.9849 0.8025 -0.0029 0.0000 -0.0174 0.1955 0.272 - 49 -11.5760 2.6879 2.3787 2.1408 0.0182 0.9854 0.8029 -0.0034 0.0000 -0.0170 0.1952 0.271 - 50 -12.4328 2.5181 2.1010 2.0025 0.0207 0.9839 0.8017 -0.0038 0.0000 -0.0165 0.1944 0.271 - 51 -13.2400 2.3582 1.8520 1.8654 0.0242 0.9788 0.7975 -0.0041 0.0000 -0.0156 0.1928 0.270 - 52 -13.9941 2.2087 1.6074 1.7271 0.0292 0.9676 0.7883 -0.0042 0.0000 -0.0143 0.1895 0.268 - 53 -14.6868 2.0715 1.3716 1.5840 0.0361 0.9462 0.7709 -0.0040 0.0000 -0.0121 0.1837 0.266 - 54 -15.3105 1.9479 1.1479 1.4304 0.0450 0.9086 0.7402 -0.0034 0.0000 -0.0090 0.1741 0.262 - 55 -15.8583 1.8393 0.9381 1.2579 0.0552 0.8460 0.6893 -0.0016 0.0000 -0.0056 0.1597 0.258 - 56 -16.3244 1.7470 0.7427 1.0604 0.0655 0.7499 0.6110 0.0045 0.0000 -0.0070 0.1435 0.261 - 57 -16.6722 1.4928 0.4131 0.8457 0.0765 1.9150 0.5732 -0.0192 0.0000 -0.0090 0.0749 0.266 - 58 -16.9098 1.1466 0.2292 0.6271 0.0919 1.8597 0.5567 -0.0448 0.0000 0.0131 0.0624 0.227 - 59 -17.0696 0.9138 0.1104 0.3878 0.1046 1.4556 0.4357 -0.0645 0.0000 0.0344 0.0373 0.171 - 60 -17.1499 0.7967 0.0322 0.1314 0.1112 0.5753 0.1722 -0.0483 0.0000 0.0226 0.0103 0.119 + 31 -0.0114 7.7520 0.3539 4.8343 0.1732 0.7201 0.5577 0.5736 0.0000 -0.0323 0.1545 0.308 + 32 -0.1025 7.6885 1.0491 4.4446 0.1729 0.7337 0.5682 0.1153 0.0000 -0.0323 0.1453 0.307 + 33 -0.2837 7.5620 1.7073 4.4108 0.1718 0.7450 0.5770 0.0868 0.0000 -0.0300 0.1446 0.302 + 34 -0.5530 7.3741 2.3052 4.3880 0.1690 0.7621 0.5903 0.0750 0.0000 -0.0265 0.1441 0.295 + 35 -0.9075 7.1267 2.8223 4.3547 0.1632 0.7838 0.6071 0.0694 0.0000 -0.0227 0.1443 0.287 + 36 -1.3432 6.8226 3.2414 4.2958 0.1504 0.8097 0.6271 0.0588 0.0000 -0.0193 0.1454 0.281 + 37 -1.8554 6.4651 3.5491 4.2047 0.1250 0.8389 0.6498 0.0446 0.0000 -0.0168 0.1476 0.276 + 38 -2.4386 6.0582 3.7368 4.0820 0.0996 0.8700 0.6739 0.0407 0.0000 -0.0151 0.1511 0.272 + 39 -3.0862 5.6062 3.8005 3.9236 0.0861 0.9051 0.7010 0.0336 0.0000 -0.0146 0.1560 0.271 + 40 -3.7613 5.1351 3.4440 3.7332 0.0740 0.9412 0.7289 0.0285 0.0000 -0.0153 0.1622 0.271 + 41 -4.4532 4.6522 3.3149 3.5340 0.0593 0.9861 0.7637 0.0134 0.0000 -0.0173 0.1705 0.273 + 42 -5.1831 4.1429 3.0930 3.2975 0.0372 1.0353 0.8018 0.0009 0.0000 -0.0184 0.1790 0.273 + 43 -6.0123 3.7903 3.4706 3.0657 0.0229 1.0009 0.8155 -0.0046 0.0000 -0.0165 0.1975 0.270 + 44 -6.9353 3.6075 3.3775 2.8862 0.0214 0.9897 0.8063 -0.0022 0.0000 -0.0167 0.1957 0.271 + 45 -7.8737 3.4215 3.2389 2.7250 0.0180 0.9851 0.8026 -0.0018 0.0000 -0.0166 0.1948 0.271 + 46 -8.8172 3.2345 3.0619 2.5735 0.0158 0.9842 0.8019 -0.0020 0.0000 -0.0163 0.1944 0.270 + 47 -9.7556 3.0486 2.8543 2.4262 0.0154 0.9845 0.8021 -0.0025 0.0000 -0.0161 0.1943 0.270 + 48 -10.6786 2.8657 2.6239 2.2826 0.0164 0.9854 0.8029 -0.0029 0.0000 -0.0158 0.1942 0.270 + 49 -11.5760 2.6879 2.3787 2.1417 0.0181 0.9858 0.8032 -0.0034 0.0000 -0.0155 0.1939 0.269 + 50 -12.4328 2.5181 2.1010 2.0032 0.0206 0.9843 0.8020 -0.0039 0.0000 -0.0149 0.1931 0.269 + 51 -13.2400 2.3582 1.8520 1.8660 0.0242 0.9791 0.7978 -0.0042 0.0000 -0.0141 0.1914 0.268 + 52 -13.9941 2.2087 1.6074 1.7277 0.0292 0.9679 0.7886 -0.0043 0.0000 -0.0127 0.1882 0.266 + 53 -14.6868 2.0715 1.3716 1.5844 0.0361 0.9464 0.7711 -0.0041 0.0000 -0.0106 0.1824 0.264 + 54 -15.3105 1.9479 1.1479 1.4305 0.0450 0.9086 0.7403 -0.0034 0.0000 -0.0074 0.1727 0.260 + 55 -15.8583 1.8393 0.9381 1.2580 0.0551 0.8460 0.6893 -0.0017 0.0000 -0.0041 0.1583 0.256 + 56 -16.3244 1.7470 0.7427 1.0600 0.0653 0.7496 0.6108 0.0044 0.0000 -0.0055 0.1421 0.259 + 57 -16.6722 1.4928 0.4131 0.8453 0.0762 1.9141 0.5730 -0.0194 0.0000 -0.0078 0.0742 0.264 + 58 -16.9098 1.1466 0.2292 0.6270 0.0919 1.8594 0.5566 -0.0450 0.0000 0.0140 0.0619 0.225 + 59 -17.0696 0.9138 0.1104 0.3878 0.1047 1.4558 0.4358 -0.0648 0.0000 0.0350 0.0371 0.170 + 60 -17.1499 0.7967 0.0322 0.1315 0.1119 0.5757 0.1723 -0.0487 0.0000 0.0228 0.0102 0.118 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04151 Clsurf = -0.00434 - CYsurf = -0.00655 Cmsurf = -0.20315 - CDsurf = 0.00310 Cnsurf = 0.00362 - CDisurf = 0.00310 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04138 Clsurf = -0.00433 + CYsurf = -0.00653 Cmsurf = -0.20252 + CDsurf = 0.00309 Cnsurf = 0.00361 + CDisurf = 0.00309 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25295 CDsurf = 0.01868 + CLsurf = 0.25215 CDsurf = 0.01862 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.9630 0.1209 0.2813 0.2147 0.1011 0.0000 -0.0111 -0.0582 0.302 - 62 0.0418 4.2566 0.2392 0.8466 0.1213 0.2584 0.1972 0.0259 0.0000 -0.0110 -0.0526 0.306 - 63 0.1156 4.2274 0.3930 0.8385 0.1214 0.2584 0.1972 0.0211 0.0000 -0.0104 -0.0520 0.303 - 64 0.2254 4.1839 0.5386 0.8360 0.1209 0.2606 0.1989 0.0199 0.0000 -0.0094 -0.0514 0.297 - 65 0.3698 4.1268 0.6730 0.8353 0.1198 0.2640 0.2015 0.0195 0.0000 -0.0081 -0.0509 0.290 - 66 0.5474 4.0565 0.7936 0.8340 0.1177 0.2683 0.2048 0.0192 0.0000 -0.0068 -0.0505 0.283 - 67 0.7617 3.9717 0.9441 0.8330 0.1145 0.2738 0.2090 0.0189 0.0000 -0.0055 -0.0504 0.276 - 68 1.0116 3.8728 1.0344 0.8314 0.1101 0.2804 0.2140 0.0188 0.0000 -0.0043 -0.0505 0.270 - 69 1.2891 3.7630 1.1046 0.8278 0.1045 0.2874 0.2193 0.0187 0.0000 -0.0034 -0.0509 0.265 - 70 1.5912 3.6435 1.1542 0.8243 0.0981 0.2956 0.2256 0.0187 0.0000 -0.0026 -0.0515 0.261 - 71 1.9146 3.5155 1.1831 0.8200 0.0918 0.3048 0.2327 0.0189 0.0000 -0.0019 -0.0525 0.258 - 72 2.2558 3.3805 1.1921 0.8141 0.0861 0.3148 0.2403 0.0189 0.0000 -0.0014 -0.0537 0.256 - 73 2.6109 3.2400 1.1821 0.8078 0.0816 0.3260 0.2488 0.0190 0.0000 -0.0009 -0.0551 0.253 - 74 2.9762 3.0955 1.1548 0.8003 0.0782 0.3382 0.2581 0.0193 0.0000 -0.0004 -0.0568 0.252 - 75 3.3476 2.9485 1.1122 0.7914 0.0758 0.3512 0.2680 0.0193 0.0000 0.0001 -0.0585 0.250 - 76 3.7210 2.8008 1.0564 0.7806 0.0741 0.3648 0.2784 0.0194 0.0000 0.0006 -0.0603 0.248 - 77 4.0924 2.6538 0.9900 0.7672 0.0730 0.3785 0.2888 0.0194 0.0000 0.0012 -0.0621 0.246 - 78 4.4577 2.5093 0.9155 0.7506 0.0726 0.3918 0.2990 0.0193 0.0000 0.0019 -0.0637 0.244 - 79 4.8128 2.3687 0.8353 0.7300 0.0727 0.4037 0.3081 0.0190 0.0000 0.0028 -0.0649 0.241 - 80 5.1540 2.2338 0.7518 0.7048 0.0735 0.4135 0.3156 0.0186 0.0000 0.0039 -0.0656 0.238 - 81 5.4774 2.1058 0.6671 0.6748 0.0749 0.4201 0.3206 0.0181 0.0000 0.0052 -0.0656 0.234 - 82 5.7795 1.9862 0.5830 0.6388 0.0770 0.4217 0.3219 0.0172 0.0000 0.0070 -0.0644 0.228 - 83 6.0570 1.8764 0.5012 0.5967 0.0797 0.4172 0.3184 0.0161 0.0000 0.0092 -0.0618 0.221 - 84 6.3069 1.7776 0.4225 0.5474 0.0828 0.4041 0.3084 0.0147 0.0000 0.0117 -0.0574 0.212 - 85 6.5264 1.6907 0.3478 0.4912 0.0860 0.3814 0.2911 0.0130 0.0000 0.0145 -0.0513 0.200 - 86 6.7314 1.6096 0.3326 0.4243 0.0894 0.3462 0.2642 0.0110 0.0000 0.0172 -0.0432 0.185 - 87 6.9144 1.5372 0.2507 0.3428 0.0926 0.2931 0.2236 0.0083 0.0000 0.0188 -0.0330 0.166 - 88 7.0535 1.4822 0.1746 0.2517 0.0952 0.2233 0.1704 0.0052 0.0000 0.0178 -0.0222 0.145 + 61 0.0047 4.2713 0.0803 0.9579 0.1210 0.2799 0.2136 0.1003 0.0000 -0.0111 -0.0580 0.302 + 62 0.0418 4.2566 0.2392 0.8427 0.1214 0.2572 0.1963 0.0258 0.0000 -0.0110 -0.0524 0.306 + 63 0.1156 4.2274 0.3930 0.8342 0.1215 0.2571 0.1962 0.0210 0.0000 -0.0104 -0.0517 0.303 + 64 0.2254 4.1839 0.5386 0.8318 0.1210 0.2592 0.1979 0.0198 0.0000 -0.0094 -0.0512 0.297 + 65 0.3698 4.1268 0.6730 0.8315 0.1199 0.2628 0.2006 0.0194 0.0000 -0.0081 -0.0507 0.290 + 66 0.5474 4.0565 0.7936 0.8305 0.1178 0.2672 0.2039 0.0191 0.0000 -0.0068 -0.0503 0.283 + 67 0.7617 3.9717 0.9441 0.8295 0.1146 0.2726 0.2081 0.0189 0.0000 -0.0055 -0.0502 0.276 + 68 1.0116 3.8728 1.0344 0.8268 0.1102 0.2788 0.2128 0.0186 0.0000 -0.0044 -0.0502 0.270 + 69 1.2891 3.7630 1.1046 0.8242 0.1046 0.2861 0.2184 0.0186 0.0000 -0.0034 -0.0506 0.266 + 70 1.5912 3.6435 1.1542 0.8207 0.0983 0.2943 0.2246 0.0186 0.0000 -0.0026 -0.0513 0.262 + 71 1.9146 3.5155 1.1831 0.8162 0.0919 0.3035 0.2316 0.0187 0.0000 -0.0019 -0.0523 0.258 + 72 2.2558 3.3805 1.1921 0.8107 0.0863 0.3135 0.2393 0.0189 0.0000 -0.0014 -0.0535 0.256 + 73 2.6109 3.2400 1.1821 0.8047 0.0818 0.3248 0.2479 0.0191 0.0000 -0.0009 -0.0550 0.254 + 74 2.9762 3.0955 1.1548 0.7977 0.0784 0.3371 0.2572 0.0193 0.0000 -0.0004 -0.0566 0.252 + 75 3.3476 2.9485 1.1122 0.7890 0.0759 0.3501 0.2672 0.0193 0.0000 0.0001 -0.0583 0.250 + 76 3.7210 2.8008 1.0564 0.7782 0.0742 0.3636 0.2775 0.0194 0.0000 0.0006 -0.0602 0.248 + 77 4.0924 2.6538 0.9900 0.7650 0.0731 0.3774 0.2880 0.0193 0.0000 0.0012 -0.0619 0.246 + 78 4.4577 2.5093 0.9155 0.7488 0.0726 0.3908 0.2983 0.0192 0.0000 0.0019 -0.0635 0.244 + 79 4.8128 2.3687 0.8353 0.7285 0.0728 0.4029 0.3075 0.0190 0.0000 0.0028 -0.0648 0.241 + 80 5.1540 2.2338 0.7518 0.7037 0.0735 0.4129 0.3151 0.0186 0.0000 0.0039 -0.0655 0.238 + 81 5.4774 2.1058 0.6671 0.6737 0.0749 0.4194 0.3201 0.0180 0.0000 0.0052 -0.0655 0.234 + 82 5.7795 1.9862 0.5830 0.6378 0.0770 0.4211 0.3214 0.0171 0.0000 0.0070 -0.0643 0.228 + 83 6.0570 1.8764 0.5012 0.5960 0.0797 0.4167 0.3180 0.0162 0.0000 0.0092 -0.0617 0.221 + 84 6.3069 1.7776 0.4225 0.5470 0.0828 0.4038 0.3082 0.0148 0.0000 0.0117 -0.0574 0.212 + 85 6.5264 1.6907 0.3478 0.4909 0.0861 0.3812 0.2909 0.0130 0.0000 0.0145 -0.0513 0.200 + 86 6.7314 1.6096 0.3326 0.4241 0.0894 0.3460 0.2641 0.0110 0.0000 0.0172 -0.0432 0.185 + 87 6.9144 1.5372 0.2507 0.3424 0.0927 0.2927 0.2234 0.0083 0.0000 0.0188 -0.0329 0.166 + 88 7.0535 1.4822 0.1746 0.2516 0.0952 0.2233 0.1704 0.0052 0.0000 0.0178 -0.0222 0.145 89 7.1471 1.4451 0.1029 0.1539 0.0970 0.1402 0.1070 0.0023 0.0000 0.0131 -0.0123 0.127 90 7.1941 1.4265 0.0340 0.0518 0.0980 0.0481 0.0367 -0.0007 0.0000 0.0049 -0.0039 0.117 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04151 Clsurf = 0.00434 - CYsurf = 0.00655 Cmsurf = -0.20315 - CDsurf = 0.00310 Cnsurf = -0.00362 - CDisurf = 0.00310 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04138 Clsurf = 0.00433 + CYsurf = 0.00653 Cmsurf = -0.20252 + CDsurf = 0.00309 Cnsurf = -0.00361 + CDisurf = 0.00309 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25295 CDsurf = 0.01868 + CLsurf = 0.25215 CDsurf = 0.01862 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.9630 0.1209 0.2813 0.2147 0.1011 0.0000 -0.0111 0.0582 0.302 - 92 -0.0418 4.2566 0.2392 0.8466 0.1213 0.2584 0.1972 0.0259 0.0000 -0.0110 0.0526 0.306 - 93 -0.1156 4.2274 0.3930 0.8385 0.1214 0.2584 0.1972 0.0211 0.0000 -0.0104 0.0520 0.303 - 94 -0.2254 4.1839 0.5386 0.8360 0.1209 0.2605 0.1989 0.0199 0.0000 -0.0094 0.0514 0.297 - 95 -0.3698 4.1268 0.6730 0.8353 0.1198 0.2640 0.2015 0.0195 0.0000 -0.0081 0.0509 0.290 - 96 -0.5474 4.0565 0.7936 0.8340 0.1177 0.2683 0.2048 0.0192 0.0000 -0.0068 0.0505 0.283 - 97 -0.7617 3.9717 0.9441 0.8330 0.1145 0.2738 0.2090 0.0189 0.0000 -0.0055 0.0504 0.276 - 98 -1.0116 3.8728 1.0344 0.8314 0.1101 0.2804 0.2140 0.0188 0.0000 -0.0043 0.0505 0.270 - 99 -1.2891 3.7630 1.1046 0.8278 0.1045 0.2874 0.2193 0.0187 0.0000 -0.0034 0.0509 0.265 - 100 -1.5912 3.6435 1.1542 0.8243 0.0981 0.2956 0.2256 0.0187 0.0000 -0.0026 0.0515 0.261 - 101 -1.9146 3.5155 1.1831 0.8200 0.0918 0.3048 0.2327 0.0189 0.0000 -0.0019 0.0525 0.258 - 102 -2.2558 3.3805 1.1921 0.8141 0.0861 0.3148 0.2403 0.0189 0.0000 -0.0014 0.0537 0.256 - 103 -2.6109 3.2400 1.1821 0.8078 0.0816 0.3260 0.2488 0.0190 0.0000 -0.0009 0.0551 0.253 - 104 -2.9762 3.0955 1.1548 0.8003 0.0782 0.3382 0.2581 0.0193 0.0000 -0.0004 0.0568 0.252 - 105 -3.3476 2.9485 1.1122 0.7914 0.0758 0.3512 0.2680 0.0193 0.0000 0.0001 0.0585 0.250 - 106 -3.7210 2.8008 1.0564 0.7806 0.0741 0.3648 0.2784 0.0194 0.0000 0.0006 0.0603 0.248 - 107 -4.0924 2.6538 0.9900 0.7671 0.0730 0.3785 0.2888 0.0194 0.0000 0.0012 0.0621 0.246 - 108 -4.4577 2.5093 0.9155 0.7506 0.0726 0.3918 0.2990 0.0193 0.0000 0.0019 0.0637 0.244 - 109 -4.8128 2.3687 0.8353 0.7300 0.0727 0.4037 0.3081 0.0190 0.0000 0.0028 0.0649 0.241 - 110 -5.1540 2.2338 0.7518 0.7048 0.0735 0.4135 0.3156 0.0186 0.0000 0.0039 0.0656 0.238 - 111 -5.4774 2.1058 0.6671 0.6748 0.0749 0.4201 0.3206 0.0181 0.0000 0.0052 0.0656 0.234 - 112 -5.7795 1.9862 0.5830 0.6387 0.0770 0.4217 0.3219 0.0172 0.0000 0.0070 0.0644 0.228 - 113 -6.0570 1.8764 0.5012 0.5967 0.0797 0.4172 0.3184 0.0161 0.0000 0.0092 0.0618 0.221 - 114 -6.3069 1.7776 0.4225 0.5473 0.0828 0.4041 0.3084 0.0147 0.0000 0.0117 0.0574 0.212 - 115 -6.5264 1.6907 0.3478 0.4912 0.0860 0.3814 0.2911 0.0130 0.0000 0.0145 0.0513 0.200 - 116 -6.7314 1.6096 0.3326 0.4243 0.0894 0.3462 0.2642 0.0110 0.0000 0.0172 0.0432 0.185 - 117 -6.9144 1.5372 0.2507 0.3428 0.0926 0.2931 0.2236 0.0083 0.0000 0.0188 0.0330 0.166 - 118 -7.0535 1.4822 0.1746 0.2517 0.0952 0.2233 0.1704 0.0052 0.0000 0.0178 0.0222 0.145 + 91 -0.0047 4.2713 0.0803 0.9579 0.1210 0.2799 0.2136 0.1003 0.0000 -0.0111 0.0580 0.302 + 92 -0.0418 4.2566 0.2392 0.8427 0.1214 0.2572 0.1963 0.0258 0.0000 -0.0110 0.0524 0.306 + 93 -0.1156 4.2274 0.3930 0.8342 0.1215 0.2571 0.1962 0.0210 0.0000 -0.0104 0.0517 0.303 + 94 -0.2254 4.1839 0.5386 0.8318 0.1210 0.2592 0.1979 0.0198 0.0000 -0.0094 0.0512 0.297 + 95 -0.3698 4.1268 0.6730 0.8315 0.1199 0.2628 0.2006 0.0194 0.0000 -0.0081 0.0507 0.290 + 96 -0.5474 4.0565 0.7936 0.8305 0.1178 0.2672 0.2039 0.0191 0.0000 -0.0068 0.0503 0.283 + 97 -0.7617 3.9717 0.9441 0.8295 0.1146 0.2726 0.2081 0.0189 0.0000 -0.0055 0.0502 0.276 + 98 -1.0116 3.8728 1.0344 0.8268 0.1102 0.2788 0.2128 0.0186 0.0000 -0.0044 0.0502 0.270 + 99 -1.2891 3.7630 1.1046 0.8242 0.1046 0.2861 0.2184 0.0186 0.0000 -0.0034 0.0506 0.266 + 100 -1.5912 3.6435 1.1542 0.8207 0.0983 0.2943 0.2246 0.0186 0.0000 -0.0026 0.0513 0.262 + 101 -1.9146 3.5155 1.1831 0.8162 0.0919 0.3035 0.2316 0.0187 0.0000 -0.0019 0.0523 0.258 + 102 -2.2558 3.3805 1.1921 0.8107 0.0863 0.3135 0.2393 0.0189 0.0000 -0.0014 0.0535 0.256 + 103 -2.6109 3.2400 1.1821 0.8047 0.0818 0.3248 0.2479 0.0191 0.0000 -0.0009 0.0550 0.254 + 104 -2.9762 3.0955 1.1548 0.7977 0.0784 0.3371 0.2572 0.0193 0.0000 -0.0004 0.0566 0.252 + 105 -3.3476 2.9485 1.1122 0.7890 0.0759 0.3501 0.2672 0.0193 0.0000 0.0001 0.0583 0.250 + 106 -3.7210 2.8008 1.0564 0.7782 0.0742 0.3636 0.2775 0.0194 0.0000 0.0006 0.0602 0.248 + 107 -4.0924 2.6538 0.9900 0.7650 0.0731 0.3774 0.2880 0.0193 0.0000 0.0012 0.0619 0.246 + 108 -4.4577 2.5093 0.9155 0.7488 0.0726 0.3908 0.2983 0.0192 0.0000 0.0019 0.0635 0.244 + 109 -4.8128 2.3687 0.8353 0.7285 0.0728 0.4029 0.3075 0.0190 0.0000 0.0028 0.0648 0.241 + 110 -5.1540 2.2338 0.7518 0.7037 0.0735 0.4129 0.3151 0.0186 0.0000 0.0039 0.0655 0.238 + 111 -5.4774 2.1058 0.6671 0.6737 0.0749 0.4194 0.3201 0.0180 0.0000 0.0052 0.0655 0.234 + 112 -5.7795 1.9862 0.5830 0.6378 0.0770 0.4211 0.3214 0.0171 0.0000 0.0070 0.0643 0.228 + 113 -6.0570 1.8764 0.5012 0.5960 0.0797 0.4167 0.3180 0.0162 0.0000 0.0092 0.0617 0.221 + 114 -6.3069 1.7776 0.4225 0.5470 0.0828 0.4038 0.3082 0.0148 0.0000 0.0117 0.0574 0.212 + 115 -6.5264 1.6907 0.3478 0.4909 0.0861 0.3812 0.2909 0.0130 0.0000 0.0145 0.0513 0.200 + 116 -6.7314 1.6096 0.3326 0.4241 0.0894 0.3460 0.2641 0.0110 0.0000 0.0172 0.0432 0.185 + 117 -6.9144 1.5372 0.2507 0.3424 0.0927 0.2927 0.2234 0.0083 0.0000 0.0188 0.0329 0.166 + 118 -7.0535 1.4822 0.1746 0.2516 0.0952 0.2233 0.1704 0.0052 0.0000 0.0178 0.0222 0.145 119 -7.1471 1.4451 0.1029 0.1539 0.0970 0.1402 0.1070 0.0023 0.0000 0.0131 0.0123 0.127 120 -7.1941 1.4265 0.0340 0.0518 0.0980 0.0481 0.0367 -0.0007 0.0000 0.0049 0.0039 0.117 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,67 +198,67 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.357 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.363 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.374 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.386 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.390 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.392 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.388 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.374 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.350 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.311 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.273 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.266 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.261 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.242 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.210 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.196 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.183 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.164 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.142 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.128 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.116 + 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.328 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.336 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.331 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.346 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.346 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.347 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.350 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.335 + 129 0.0000 5.8609 2.1733 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.318 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.285 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.251 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.246 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.219 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.207 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.195 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.177 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.159 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.138 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.118 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.109 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01091 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.06674 + CLsurf = 0.01084 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.06681 CDsurf = -0.00025 Cnsurf = -0.00000 CDisurf = -0.00025 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01100 CDsurf = -0.00025 + CLsurf = 0.01093 CDsurf = -0.00025 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.2480 0.1786 0.1050 0.0098 -0.0030 0.0000 0.0048 0.0003 -0.238 - 152 -1.3090 31.2096 11.6724 0.3507 0.1914 0.0428 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.268 - 153 -0.9350 34.0626 12.7394 0.3850 0.1770 0.0273 0.0114 -0.0002 0.0000 0.0071 0.0014 -0.370 - 154 -0.5610 36.1619 13.5246 0.4038 0.1721 0.0186 0.0112 0.0005 0.0000 0.0076 0.0022 -0.431 - 155 -0.1870 37.5332 14.0374 0.4144 0.1721 0.0127 0.0109 0.0016 0.0000 0.0077 0.0034 -0.459 - 156 0.1870 37.5332 14.0374 0.4144 0.1721 0.0127 0.0109 0.0016 0.0000 0.0077 0.0034 -0.459 - 157 0.5610 36.1619 13.5246 0.4038 0.1721 0.0186 0.0112 0.0005 0.0000 0.0076 0.0022 -0.431 - 158 0.9350 34.0626 12.7394 0.3850 0.1770 0.0273 0.0114 -0.0002 0.0000 0.0071 0.0014 -0.370 - 159 1.3090 31.2096 11.6724 0.3507 0.1914 0.0428 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.268 - 160 1.6830 26.5957 9.9468 0.2480 0.1786 0.1050 0.0098 -0.0030 0.0000 0.0048 0.0003 -0.238 + 151 -1.6830 26.5957 9.9468 0.2462 0.1785 0.1043 0.0097 -0.0030 0.0000 0.0048 0.0003 -0.244 + 152 -1.3090 31.2096 11.6724 0.3483 0.1914 0.0425 0.0114 -0.0010 0.0000 0.0060 0.0008 -0.274 + 153 -0.9350 34.0626 12.7394 0.3825 0.1772 0.0271 0.0113 -0.0002 0.0000 0.0071 0.0014 -0.376 + 154 -0.5610 36.1619 13.5246 0.4013 0.1723 0.0185 0.0111 0.0005 0.0000 0.0076 0.0022 -0.436 + 155 -0.1870 37.5332 14.0374 0.4118 0.1723 0.0126 0.0109 0.0016 0.0000 0.0078 0.0035 -0.465 + 156 0.1870 37.5332 14.0374 0.4118 0.1723 0.0126 0.0109 0.0016 0.0000 0.0078 0.0035 -0.465 + 157 0.5610 36.1619 13.5246 0.4013 0.1723 0.0185 0.0111 0.0005 0.0000 0.0076 0.0022 -0.436 + 158 0.9350 34.0626 12.7394 0.3825 0.1772 0.0271 0.0113 -0.0002 0.0000 0.0071 0.0014 -0.376 + 159 1.3090 31.2096 11.6724 0.3483 0.1914 0.0425 0.0114 -0.0010 0.0000 0.0060 0.0008 -0.274 + 160 1.6830 26.5957 9.9468 0.2462 0.1785 0.1043 0.0097 -0.0030 0.0000 0.0048 0.0003 -0.244 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 + CLsurf = 0.00000 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = 0.00000 Cnsurf = -0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0002 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.596 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.207 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.081 - 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.420 - 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.502 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.573 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.640 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.732 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.777 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.404 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.103 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.087 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.498 + 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.577 + 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.619 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.667 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.742 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_01_06.txt b/regression/scripts/AVL/avl_files/strip_forces_case_01_06.txt index 0f738a5f68..f43b6b325c 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_01_06.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_01_06.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.49144 Clsurf = -0.09618 - CYsurf = -0.02241 Cmsurf = -0.44200 - CDsurf = 0.02094 Cnsurf = -0.01503 - CDisurf = 0.02094 CDvsurf = 0.00000 + CLsurf = 0.49216 Clsurf = -0.09625 + CYsurf = -0.02200 Cmsurf = -0.44235 + CDsurf = 0.02029 Cnsurf = -0.01507 + CDisurf = 0.02029 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.96000 CDsurf = 0.04087 + CLsurf = 0.96134 CDsurf = 0.03961 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 6.2599 0.2260 0.8457 0.6564 0.9247 0.0000 -0.0391 -0.1986 0.310 - 2 0.1025 7.6885 1.0492 5.6291 0.2259 0.9162 0.7111 0.1830 0.0000 -0.0396 -0.1837 0.306 - 3 0.2837 7.5620 1.7073 5.5768 0.2246 0.9337 0.7246 0.1369 0.0000 -0.0367 -0.1824 0.301 - 4 0.5530 7.3741 2.3052 5.5509 0.2215 0.9569 0.7427 0.1225 0.0000 -0.0321 -0.1819 0.293 - 5 0.9075 7.1267 2.8223 5.5088 0.2144 0.9864 0.7656 0.1094 0.0000 -0.0272 -0.1821 0.286 - 6 1.3432 6.8226 3.2414 5.4445 0.1972 1.0222 0.7933 0.0960 0.0000 -0.0227 -0.1836 0.279 - 7 1.8554 6.4651 3.5491 5.3626 0.1601 1.0649 0.8265 0.0894 0.0000 -0.0188 -0.1870 0.273 - 8 2.4386 6.0582 3.7368 5.2105 0.1238 1.1087 0.8605 0.0727 0.0000 -0.0169 -0.1918 0.270 - 9 3.0862 5.6062 3.8005 5.0269 0.1081 1.1598 0.9001 0.0586 0.0000 -0.0161 -0.1987 0.268 - 10 3.7613 5.1351 3.4440 4.8060 0.0957 1.2151 0.9430 0.0417 0.0000 -0.0169 -0.2075 0.268 - 11 4.4532 4.6522 3.3149 4.5784 0.0798 1.2813 0.9944 0.0281 0.0000 -0.0187 -0.2189 0.269 - 12 5.1831 4.1429 3.0930 4.3085 0.0546 1.3592 1.0548 0.0068 0.0000 -0.0206 -0.2321 0.270 - 13 6.0123 3.7903 3.4706 4.0361 0.0370 1.3293 1.0816 -0.0017 0.0000 -0.0158 -0.2567 0.265 - 14 6.9353 3.6075 3.3775 3.8181 0.0333 1.3206 1.0746 0.0011 0.0000 -0.0160 -0.2554 0.265 - 15 7.8737 3.4215 3.2389 3.6190 0.0275 1.3198 1.0739 0.0009 0.0000 -0.0158 -0.2551 0.265 - 16 8.8172 3.2345 3.0619 3.4281 0.0237 1.3227 1.0763 -0.0002 0.0000 -0.0156 -0.2553 0.264 - 17 9.7556 3.0486 2.8543 3.2405 0.0228 1.3268 1.0796 -0.0014 0.0000 -0.0153 -0.2558 0.264 - 18 10.6786 2.8657 2.6240 3.0550 0.0238 1.3310 1.0830 -0.0027 0.0000 -0.0149 -0.2562 0.264 - 19 11.5760 2.6879 2.3787 2.8714 0.0261 1.3341 1.0855 -0.0039 0.0000 -0.0144 -0.2562 0.263 - 20 12.4328 2.5181 2.1010 2.6895 0.0295 1.3340 1.0855 -0.0050 0.0000 -0.0137 -0.2555 0.263 - 21 13.2400 2.3582 1.8520 2.5080 0.0342 1.3286 1.0810 -0.0058 0.0000 -0.0125 -0.2535 0.262 - 22 13.9941 2.2087 1.6074 2.3240 0.0410 1.3145 1.0696 -0.0062 0.0000 -0.0107 -0.2493 0.260 - 23 14.6868 2.0715 1.3716 2.1325 0.0503 1.2861 1.0465 -0.0060 0.0000 -0.0078 -0.2416 0.257 - 24 15.3105 1.9479 1.1479 1.9263 0.0623 1.2352 1.0051 -0.0051 0.0000 -0.0036 -0.2287 0.254 - 25 15.8583 1.8393 0.9381 1.6939 0.0759 1.1498 0.9356 -0.0021 0.0000 0.0007 -0.2094 0.249 - 26 16.3244 1.7470 0.7427 1.4274 0.0898 1.0177 0.8281 0.0092 0.0000 -0.0018 -0.1879 0.252 - 27 16.6722 1.4928 0.4131 1.1372 0.1043 2.5526 0.7801 -0.0352 0.0000 -0.0054 -0.1002 0.257 - 28 16.9098 1.1466 0.2292 0.8425 0.1243 2.4906 0.7612 -0.0823 0.0000 0.0239 -0.0835 0.219 - 29 17.0696 0.9138 0.1104 0.5205 0.1405 1.9635 0.6001 -0.1190 0.0000 0.0514 -0.0499 0.164 - 30 17.1499 0.7967 0.0322 0.1762 0.1489 0.7890 0.2411 -0.0909 0.0000 0.0327 -0.0137 0.115 + 1 0.0114 7.7520 0.3539 6.2775 0.2261 0.8485 0.6586 0.9254 0.0000 -0.0406 -0.2003 0.312 + 2 0.1025 7.6885 1.0491 5.6442 0.2260 0.9187 0.7131 0.1831 0.0000 -0.0409 -0.1851 0.307 + 3 0.2837 7.5620 1.7073 5.5919 0.2249 0.9362 0.7266 0.1370 0.0000 -0.0379 -0.1838 0.302 + 4 0.5530 7.3741 2.3052 5.5626 0.2220 0.9599 0.7450 0.1186 0.0000 -0.0334 -0.1833 0.295 + 5 0.9075 7.1267 2.8223 5.5250 0.2150 0.9892 0.7677 0.1103 0.0000 -0.0284 -0.1836 0.287 + 6 1.3432 6.8226 3.2414 5.4579 0.1978 1.0252 0.7957 0.0940 0.0000 -0.0240 -0.1851 0.280 + 7 1.8554 6.4651 3.5491 5.3536 0.1607 1.0670 0.8281 0.0719 0.0000 -0.0206 -0.1881 0.275 + 8 2.4386 6.0582 3.7368 5.2156 0.1244 1.1112 0.8624 0.0668 0.0000 -0.0181 -0.1929 0.271 + 9 3.0862 5.6062 3.8005 5.0378 0.1089 1.1628 0.9024 0.0567 0.0000 -0.0170 -0.1998 0.269 + 10 3.7613 5.1351 3.4440 4.8206 0.0962 1.2169 0.9444 0.0498 0.0000 -0.0174 -0.2085 0.268 + 11 4.4532 4.6522 3.3149 4.5973 0.0797 1.2869 0.9988 0.0266 0.0000 -0.0192 -0.2202 0.269 + 12 5.1831 4.1429 3.0930 4.3203 0.0540 1.3628 1.0576 0.0073 0.0000 -0.0192 -0.2314 0.268 + 13 6.0123 3.7903 3.4706 4.0386 0.0366 1.3301 1.0823 -0.0017 0.0000 -0.0144 -0.2556 0.263 + 14 6.9353 3.6075 3.3775 3.8196 0.0331 1.3212 1.0750 0.0011 0.0000 -0.0145 -0.2542 0.264 + 15 7.8737 3.4215 3.2389 3.6202 0.0273 1.3203 1.0743 0.0009 0.0000 -0.0143 -0.2538 0.263 + 16 8.8172 3.2345 3.0619 3.4301 0.0236 1.3235 1.0769 -0.0002 0.0000 -0.0140 -0.2541 0.263 + 17 9.7556 3.0486 2.8543 3.2417 0.0227 1.3274 1.0801 -0.0015 0.0000 -0.0137 -0.2545 0.263 + 18 10.6786 2.8657 2.6239 3.0561 0.0238 1.3315 1.0834 -0.0027 0.0000 -0.0134 -0.2549 0.262 + 19 11.5760 2.6879 2.3787 2.8723 0.0260 1.3345 1.0858 -0.0040 0.0000 -0.0129 -0.2550 0.262 + 20 12.4328 2.5181 2.1010 2.6902 0.0294 1.3344 1.0858 -0.0051 0.0000 -0.0121 -0.2542 0.261 + 21 13.2400 2.3582 1.8520 2.5086 0.0342 1.3289 1.0813 -0.0059 0.0000 -0.0110 -0.2522 0.260 + 22 13.9941 2.2087 1.6074 2.3245 0.0410 1.3148 1.0698 -0.0063 0.0000 -0.0092 -0.2480 0.259 + 23 14.6868 2.0715 1.3716 2.1329 0.0503 1.2863 1.0467 -0.0061 0.0000 -0.0063 -0.2403 0.256 + 24 15.3105 1.9479 1.1479 1.9263 0.0623 1.2353 1.0051 -0.0052 0.0000 -0.0021 -0.2273 0.252 + 25 15.8583 1.8393 0.9381 1.6941 0.0759 1.1499 0.9357 -0.0022 0.0000 0.0022 -0.2080 0.248 + 26 16.3244 1.7470 0.7427 1.4269 0.0895 1.0174 0.8278 0.0091 0.0000 -0.0003 -0.1865 0.250 + 27 16.6722 1.4928 0.4131 1.1367 0.1040 2.5518 0.7799 -0.0356 0.0000 -0.0042 -0.0996 0.255 + 28 16.9098 1.1466 0.2292 0.8424 0.1242 2.4903 0.7611 -0.0826 0.0000 0.0249 -0.0830 0.217 + 29 17.0696 0.9138 0.1104 0.5205 0.1406 1.9637 0.6002 -0.1194 0.0000 0.0520 -0.0497 0.163 + 30 17.1499 0.7967 0.0322 0.1763 0.1496 0.7895 0.2413 -0.0914 0.0000 0.0328 -0.0136 0.114 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.49144 Clsurf = 0.09618 - CYsurf = 0.02241 Cmsurf = -0.44199 - CDsurf = 0.02094 Cnsurf = 0.01503 - CDisurf = 0.02094 CDvsurf = 0.00000 + CLsurf = 0.49216 Clsurf = 0.09625 + CYsurf = 0.02200 Cmsurf = -0.44235 + CDsurf = 0.02029 Cnsurf = 0.01507 + CDisurf = 0.02029 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.96000 CDsurf = 0.04087 + CLsurf = 0.96134 CDsurf = 0.03961 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 6.2599 0.2263 0.8457 0.6564 0.9248 0.0000 -0.0391 0.1986 0.310 - 32 -0.1025 7.6885 1.0492 5.6291 0.2259 0.9162 0.7111 0.1830 0.0000 -0.0396 0.1837 0.306 - 33 -0.2837 7.5620 1.7073 5.5768 0.2246 0.9337 0.7246 0.1369 0.0000 -0.0367 0.1824 0.301 - 34 -0.5530 7.3741 2.3052 5.5509 0.2215 0.9569 0.7427 0.1225 0.0000 -0.0321 0.1819 0.293 - 35 -0.9075 7.1267 2.8223 5.5088 0.2144 0.9864 0.7656 0.1094 0.0000 -0.0272 0.1821 0.286 - 36 -1.3432 6.8226 3.2414 5.4444 0.1972 1.0222 0.7933 0.0960 0.0000 -0.0227 0.1836 0.279 - 37 -1.8554 6.4651 3.5491 5.3626 0.1601 1.0648 0.8264 0.0894 0.0000 -0.0188 0.1870 0.273 - 38 -2.4386 6.0582 3.7368 5.2105 0.1238 1.1087 0.8605 0.0727 0.0000 -0.0169 0.1918 0.270 - 39 -3.0862 5.6062 3.8005 5.0269 0.1081 1.1598 0.9001 0.0586 0.0000 -0.0161 0.1987 0.268 - 40 -3.7613 5.1351 3.4440 4.8060 0.0957 1.2151 0.9430 0.0417 0.0000 -0.0169 0.2075 0.268 - 41 -4.4532 4.6522 3.3149 4.5784 0.0798 1.2813 0.9944 0.0281 0.0000 -0.0187 0.2189 0.269 - 42 -5.1831 4.1429 3.0930 4.3085 0.0546 1.3592 1.0548 0.0068 0.0000 -0.0206 0.2321 0.270 - 43 -6.0123 3.7903 3.4706 4.0361 0.0370 1.3293 1.0816 -0.0017 0.0000 -0.0158 0.2567 0.265 - 44 -6.9353 3.6075 3.3775 3.8181 0.0333 1.3206 1.0746 0.0011 0.0000 -0.0160 0.2554 0.265 - 45 -7.8737 3.4215 3.2389 3.6190 0.0275 1.3198 1.0739 0.0009 0.0000 -0.0158 0.2551 0.265 - 46 -8.8172 3.2345 3.0619 3.4281 0.0237 1.3227 1.0763 -0.0002 0.0000 -0.0156 0.2553 0.264 - 47 -9.7556 3.0486 2.8543 3.2404 0.0228 1.3268 1.0796 -0.0014 0.0000 -0.0153 0.2558 0.264 - 48 -10.6786 2.8657 2.6240 3.0550 0.0238 1.3310 1.0830 -0.0027 0.0000 -0.0149 0.2562 0.264 - 49 -11.5760 2.6879 2.3787 2.8714 0.0261 1.3340 1.0855 -0.0039 0.0000 -0.0144 0.2562 0.263 - 50 -12.4328 2.5181 2.1010 2.6895 0.0294 1.3340 1.0855 -0.0050 0.0000 -0.0137 0.2555 0.263 - 51 -13.2400 2.3582 1.8520 2.5080 0.0342 1.3285 1.0810 -0.0058 0.0000 -0.0125 0.2535 0.262 - 52 -13.9941 2.2087 1.6074 2.3239 0.0410 1.3144 1.0695 -0.0062 0.0000 -0.0107 0.2493 0.260 - 53 -14.6868 2.0715 1.3716 2.1325 0.0503 1.2861 1.0464 -0.0060 0.0000 -0.0078 0.2416 0.257 - 54 -15.3105 1.9479 1.1479 1.9262 0.0623 1.2352 1.0051 -0.0051 0.0000 -0.0036 0.2287 0.254 - 55 -15.8583 1.8393 0.9381 1.6939 0.0759 1.1498 0.9356 -0.0021 0.0000 0.0007 0.2094 0.249 - 56 -16.3244 1.7470 0.7427 1.4274 0.0898 1.0177 0.8281 0.0092 0.0000 -0.0018 0.1879 0.252 - 57 -16.6722 1.4928 0.4131 1.1372 0.1043 2.5526 0.7801 -0.0352 0.0000 -0.0054 0.1002 0.257 - 58 -16.9098 1.1466 0.2292 0.8425 0.1243 2.4905 0.7612 -0.0823 0.0000 0.0239 0.0835 0.219 - 59 -17.0696 0.9138 0.1104 0.5205 0.1405 1.9634 0.6001 -0.1190 0.0000 0.0514 0.0499 0.164 - 60 -17.1499 0.7967 0.0322 0.1762 0.1489 0.7890 0.2411 -0.0909 0.0000 0.0327 0.0137 0.115 + 31 -0.0114 7.7520 0.3539 6.2775 0.2261 0.8485 0.6586 0.9254 0.0000 -0.0406 0.2003 0.312 + 32 -0.1025 7.6885 1.0491 5.6442 0.2260 0.9187 0.7131 0.1831 0.0000 -0.0409 0.1851 0.307 + 33 -0.2837 7.5620 1.7073 5.5919 0.2249 0.9362 0.7266 0.1370 0.0000 -0.0379 0.1838 0.302 + 34 -0.5530 7.3741 2.3052 5.5626 0.2220 0.9599 0.7450 0.1186 0.0000 -0.0334 0.1833 0.295 + 35 -0.9075 7.1267 2.8223 5.5250 0.2150 0.9892 0.7677 0.1103 0.0000 -0.0284 0.1836 0.287 + 36 -1.3432 6.8226 3.2414 5.4579 0.1978 1.0252 0.7957 0.0940 0.0000 -0.0240 0.1851 0.280 + 37 -1.8554 6.4651 3.5491 5.3536 0.1607 1.0670 0.8281 0.0719 0.0000 -0.0206 0.1881 0.275 + 38 -2.4386 6.0582 3.7368 5.2156 0.1244 1.1112 0.8624 0.0668 0.0000 -0.0181 0.1929 0.271 + 39 -3.0862 5.6062 3.8005 5.0378 0.1089 1.1628 0.9024 0.0567 0.0000 -0.0170 0.1998 0.269 + 40 -3.7613 5.1351 3.4440 4.8206 0.0962 1.2169 0.9444 0.0498 0.0000 -0.0174 0.2085 0.268 + 41 -4.4532 4.6522 3.3149 4.5973 0.0797 1.2869 0.9988 0.0266 0.0000 -0.0192 0.2202 0.269 + 42 -5.1831 4.1429 3.0930 4.3203 0.0540 1.3628 1.0576 0.0073 0.0000 -0.0192 0.2314 0.268 + 43 -6.0123 3.7903 3.4706 4.0386 0.0366 1.3301 1.0823 -0.0017 0.0000 -0.0144 0.2556 0.263 + 44 -6.9353 3.6075 3.3775 3.8196 0.0331 1.3212 1.0750 0.0011 0.0000 -0.0145 0.2542 0.264 + 45 -7.8737 3.4215 3.2389 3.6202 0.0273 1.3203 1.0743 0.0009 0.0000 -0.0143 0.2538 0.263 + 46 -8.8172 3.2345 3.0619 3.4300 0.0236 1.3235 1.0769 -0.0002 0.0000 -0.0140 0.2541 0.263 + 47 -9.7556 3.0486 2.8543 3.2417 0.0227 1.3274 1.0801 -0.0015 0.0000 -0.0137 0.2545 0.263 + 48 -10.6786 2.8657 2.6239 3.0561 0.0238 1.3315 1.0834 -0.0027 0.0000 -0.0134 0.2549 0.262 + 49 -11.5760 2.6879 2.3787 2.8723 0.0260 1.3345 1.0858 -0.0040 0.0000 -0.0129 0.2550 0.262 + 50 -12.4328 2.5181 2.1010 2.6902 0.0294 1.3344 1.0858 -0.0051 0.0000 -0.0121 0.2542 0.261 + 51 -13.2400 2.3582 1.8520 2.5086 0.0342 1.3289 1.0813 -0.0059 0.0000 -0.0110 0.2522 0.260 + 52 -13.9941 2.2087 1.6074 2.3245 0.0410 1.3148 1.0698 -0.0063 0.0000 -0.0092 0.2480 0.259 + 53 -14.6868 2.0715 1.3716 2.1329 0.0503 1.2863 1.0467 -0.0061 0.0000 -0.0063 0.2403 0.256 + 54 -15.3105 1.9479 1.1479 1.9263 0.0623 1.2353 1.0051 -0.0052 0.0000 -0.0021 0.2273 0.252 + 55 -15.8583 1.8393 0.9381 1.6941 0.0759 1.1499 0.9357 -0.0022 0.0000 0.0022 0.2080 0.248 + 56 -16.3244 1.7470 0.7427 1.4269 0.0895 1.0174 0.8278 0.0091 0.0000 -0.0003 0.1865 0.250 + 57 -16.6722 1.4928 0.4131 1.1367 0.1040 2.5518 0.7799 -0.0356 0.0000 -0.0042 0.0996 0.255 + 58 -16.9098 1.1466 0.2292 0.8424 0.1242 2.4903 0.7611 -0.0826 0.0000 0.0249 0.0830 0.217 + 59 -17.0696 0.9138 0.1104 0.5205 0.1406 1.9637 0.6002 -0.1194 0.0000 0.0520 0.0497 0.163 + 60 -17.1499 0.7967 0.0322 0.1763 0.1496 0.7895 0.2413 -0.0914 0.0000 0.0328 0.0136 0.114 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06405 Clsurf = -0.00659 - CYsurf = -0.01006 Cmsurf = -0.31426 - CDsurf = 0.00649 Cnsurf = 0.00531 - CDisurf = 0.00649 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06391 Clsurf = -0.00657 + CYsurf = -0.01004 Cmsurf = -0.31361 + CDsurf = 0.00647 Cnsurf = 0.00529 + CDisurf = 0.00647 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39023 CDsurf = 0.03904 + CLsurf = 0.38940 CDsurf = 0.03894 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.6493 0.1676 0.4571 0.3475 0.2521 0.0000 -0.0162 -0.0982 0.297 - 62 0.0418 4.2566 0.2392 1.3532 0.1683 0.4109 0.3123 0.0591 0.0000 -0.0164 -0.0839 0.302 - 63 0.1156 4.2274 0.3930 1.3322 0.1686 0.4100 0.3117 0.0468 0.0000 -0.0154 -0.0825 0.299 - 64 0.2254 4.1839 0.5386 1.3255 0.1680 0.4130 0.3139 0.0437 0.0000 -0.0137 -0.0815 0.294 - 65 0.3698 4.1268 0.6730 1.3232 0.1665 0.4184 0.3180 0.0425 0.0000 -0.0117 -0.0807 0.287 - 66 0.5474 4.0565 0.7936 1.3196 0.1636 0.4248 0.3229 0.0417 0.0000 -0.0096 -0.0800 0.280 - 67 0.7617 3.9717 0.9441 1.3169 0.1592 0.4334 0.3295 0.0406 0.0000 -0.0075 -0.0797 0.273 - 68 1.0116 3.8728 1.0344 1.3134 0.1528 0.4437 0.3372 0.0401 0.0000 -0.0057 -0.0798 0.267 - 69 1.2891 3.7630 1.1046 1.3049 0.1447 0.4540 0.3450 0.0398 0.0000 -0.0042 -0.0803 0.262 - 70 1.5912 3.6435 1.1542 1.2972 0.1354 0.4664 0.3545 0.0395 0.0000 -0.0029 -0.0812 0.258 - 71 1.9146 3.5155 1.1831 1.2876 0.1262 0.4800 0.3649 0.0396 0.0000 -0.0018 -0.0826 0.255 - 72 2.2558 3.3805 1.1921 1.2741 0.1180 0.4943 0.3757 0.0394 0.0000 -0.0009 -0.0842 0.252 - 73 2.6109 3.2400 1.1821 1.2597 0.1116 0.5102 0.3878 0.0395 0.0000 -0.0001 -0.0862 0.250 - 74 2.9762 3.0955 1.1548 1.2427 0.1070 0.5270 0.4006 0.0399 0.0000 0.0006 -0.0884 0.249 - 75 3.3476 2.9485 1.1122 1.2233 0.1038 0.5450 0.4142 0.0396 0.0000 0.0013 -0.0908 0.247 - 76 3.7210 2.8008 1.0564 1.2008 0.1017 0.5635 0.4283 0.0396 0.0000 0.0021 -0.0932 0.245 - 77 4.0924 2.6538 0.9900 1.1741 0.1005 0.5818 0.4422 0.0395 0.0000 0.0029 -0.0955 0.243 - 78 4.4577 2.5093 0.9155 1.1431 0.1002 0.5994 0.4556 0.0391 0.0000 0.0039 -0.0976 0.241 - 79 4.8128 2.3687 0.8353 1.1062 0.1006 0.6149 0.4674 0.0384 0.0000 0.0052 -0.0991 0.239 - 80 5.1540 2.2338 0.7518 1.0631 0.1020 0.6270 0.4766 0.0374 0.0000 0.0067 -0.0998 0.236 - 81 5.4774 2.1058 0.6671 1.0139 0.1043 0.6347 0.4824 0.0363 0.0000 0.0087 -0.0993 0.232 - 82 5.7795 1.9862 0.5830 0.9560 0.1075 0.6349 0.4826 0.0343 0.0000 0.0112 -0.0972 0.227 - 83 6.0570 1.8764 0.5012 0.8904 0.1116 0.6264 0.4761 0.0322 0.0000 0.0144 -0.0931 0.220 - 84 6.3069 1.7776 0.4225 0.8143 0.1163 0.6051 0.4600 0.0292 0.0000 0.0181 -0.0864 0.211 - 85 6.5264 1.6907 0.3478 0.7292 0.1212 0.5701 0.4333 0.0258 0.0000 0.0221 -0.0771 0.199 - 86 6.7314 1.6096 0.3326 0.6288 0.1262 0.5168 0.3928 0.0217 0.0000 0.0259 -0.0650 0.184 - 87 6.9144 1.5372 0.2507 0.5074 0.1310 0.4372 0.3323 0.0162 0.0000 0.0283 -0.0496 0.165 + 61 0.0047 4.2713 0.0803 1.6437 0.1677 0.4556 0.3464 0.2508 0.0000 -0.0162 -0.0979 0.297 + 62 0.0418 4.2566 0.2392 1.3494 0.1684 0.4097 0.3114 0.0590 0.0000 -0.0163 -0.0837 0.302 + 63 0.1156 4.2274 0.3930 1.3275 0.1686 0.4086 0.3106 0.0466 0.0000 -0.0154 -0.0823 0.299 + 64 0.2254 4.1839 0.5386 1.3209 0.1681 0.4116 0.3129 0.0434 0.0000 -0.0137 -0.0813 0.294 + 65 0.3698 4.1268 0.6730 1.3196 0.1666 0.4173 0.3172 0.0423 0.0000 -0.0117 -0.0805 0.287 + 66 0.5474 4.0565 0.7936 1.3167 0.1637 0.4239 0.3222 0.0415 0.0000 -0.0096 -0.0798 0.280 + 67 0.7617 3.9717 0.9441 1.3139 0.1592 0.4324 0.3287 0.0408 0.0000 -0.0076 -0.0795 0.273 + 68 1.0116 3.8728 1.0344 1.3073 0.1529 0.4416 0.3357 0.0397 0.0000 -0.0057 -0.0795 0.267 + 69 1.2891 3.7630 1.1046 1.3016 0.1448 0.4528 0.3442 0.0395 0.0000 -0.0041 -0.0801 0.262 + 70 1.5912 3.6435 1.1542 1.2937 0.1355 0.4651 0.3535 0.0393 0.0000 -0.0029 -0.0810 0.258 + 71 1.9146 3.5155 1.1831 1.2833 0.1263 0.4785 0.3637 0.0393 0.0000 -0.0018 -0.0824 0.255 + 72 2.2558 3.3805 1.1921 1.2705 0.1181 0.4928 0.3746 0.0394 0.0000 -0.0009 -0.0840 0.253 + 73 2.6109 3.2400 1.1821 1.2565 0.1118 0.5088 0.3867 0.0396 0.0000 -0.0002 -0.0860 0.250 + 74 2.9762 3.0955 1.1548 1.2404 0.1071 0.5260 0.3998 0.0398 0.0000 0.0006 -0.0883 0.249 + 75 3.3476 2.9485 1.1122 1.2210 0.1039 0.5439 0.4134 0.0397 0.0000 0.0013 -0.0906 0.247 + 76 3.7210 2.8008 1.0564 1.1980 0.1018 0.5622 0.4273 0.0396 0.0000 0.0020 -0.0930 0.245 + 77 4.0924 2.6538 0.9900 1.1716 0.1006 0.5806 0.4413 0.0393 0.0000 0.0029 -0.0954 0.243 + 78 4.4577 2.5093 0.9155 1.1412 0.1002 0.5984 0.4549 0.0389 0.0000 0.0039 -0.0974 0.241 + 79 4.8128 2.3687 0.8353 1.1047 0.1007 0.6141 0.4667 0.0383 0.0000 0.0052 -0.0990 0.239 + 80 5.1540 2.2338 0.7518 1.0621 0.1020 0.6265 0.4762 0.0374 0.0000 0.0067 -0.0997 0.236 + 81 5.4774 2.1058 0.6671 1.0125 0.1043 0.6339 0.4818 0.0361 0.0000 0.0087 -0.0992 0.232 + 82 5.7795 1.9862 0.5830 0.9548 0.1076 0.6342 0.4821 0.0340 0.0000 0.0112 -0.0971 0.227 + 83 6.0570 1.8764 0.5012 0.8896 0.1116 0.6258 0.4756 0.0322 0.0000 0.0144 -0.0930 0.220 + 84 6.3069 1.7776 0.4225 0.8142 0.1163 0.6050 0.4598 0.0295 0.0000 0.0181 -0.0863 0.211 + 85 6.5264 1.6907 0.3478 0.7291 0.1212 0.5700 0.4333 0.0258 0.0000 0.0221 -0.0771 0.199 + 86 6.7314 1.6096 0.3326 0.6288 0.1262 0.5168 0.3928 0.0216 0.0000 0.0259 -0.0649 0.184 + 87 6.9144 1.5372 0.2507 0.5068 0.1311 0.4367 0.3319 0.0161 0.0000 0.0282 -0.0496 0.165 88 7.0535 1.4822 0.1746 0.3720 0.1349 0.3330 0.2531 0.0100 0.0000 0.0266 -0.0334 0.145 89 7.1471 1.4451 0.1029 0.2273 0.1376 0.2092 0.1590 0.0042 0.0000 0.0196 -0.0186 0.127 - 90 7.1941 1.4265 0.0340 0.0766 0.1391 0.0721 0.0548 -0.0017 0.0000 0.0073 -0.0059 0.118 + 90 7.1941 1.4265 0.0340 0.0766 0.1391 0.0721 0.0548 -0.0017 0.0000 0.0073 -0.0059 0.117 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06405 Clsurf = 0.00659 - CYsurf = 0.01006 Cmsurf = -0.31426 - CDsurf = 0.00649 Cnsurf = -0.00531 - CDisurf = 0.00649 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06391 Clsurf = 0.00657 + CYsurf = 0.01004 Cmsurf = -0.31361 + CDsurf = 0.00647 Cnsurf = -0.00529 + CDisurf = 0.00647 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39022 CDsurf = 0.03904 + CLsurf = 0.38940 CDsurf = 0.03894 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.6493 0.1676 0.4571 0.3475 0.2521 0.0000 -0.0162 0.0982 0.297 - 92 -0.0418 4.2566 0.2392 1.3532 0.1683 0.4109 0.3123 0.0591 0.0000 -0.0164 0.0839 0.302 - 93 -0.1156 4.2274 0.3930 1.3322 0.1686 0.4100 0.3117 0.0468 0.0000 -0.0154 0.0825 0.299 - 94 -0.2254 4.1839 0.5386 1.3255 0.1680 0.4130 0.3139 0.0437 0.0000 -0.0137 0.0815 0.294 - 95 -0.3698 4.1268 0.6730 1.3232 0.1665 0.4184 0.3180 0.0425 0.0000 -0.0117 0.0807 0.287 - 96 -0.5474 4.0565 0.7936 1.3196 0.1636 0.4248 0.3229 0.0417 0.0000 -0.0096 0.0800 0.280 - 97 -0.7617 3.9717 0.9441 1.3169 0.1592 0.4334 0.3295 0.0406 0.0000 -0.0075 0.0797 0.273 - 98 -1.0116 3.8728 1.0344 1.3134 0.1528 0.4436 0.3372 0.0401 0.0000 -0.0057 0.0798 0.267 - 99 -1.2891 3.7630 1.1046 1.3049 0.1446 0.4540 0.3450 0.0398 0.0000 -0.0042 0.0803 0.262 - 100 -1.5912 3.6435 1.1542 1.2972 0.1354 0.4664 0.3545 0.0395 0.0000 -0.0029 0.0812 0.258 - 101 -1.9146 3.5155 1.1831 1.2876 0.1262 0.4800 0.3649 0.0396 0.0000 -0.0018 0.0826 0.255 - 102 -2.2558 3.3805 1.1921 1.2741 0.1180 0.4943 0.3757 0.0394 0.0000 -0.0009 0.0842 0.252 - 103 -2.6109 3.2400 1.1821 1.2597 0.1116 0.5102 0.3878 0.0395 0.0000 -0.0001 0.0862 0.250 - 104 -2.9762 3.0955 1.1548 1.2427 0.1070 0.5270 0.4006 0.0399 0.0000 0.0006 0.0884 0.249 - 105 -3.3476 2.9485 1.1122 1.2233 0.1038 0.5450 0.4142 0.0396 0.0000 0.0013 0.0908 0.247 - 106 -3.7210 2.8008 1.0564 1.2008 0.1017 0.5635 0.4283 0.0396 0.0000 0.0021 0.0932 0.245 - 107 -4.0924 2.6538 0.9900 1.1741 0.1005 0.5818 0.4422 0.0395 0.0000 0.0029 0.0955 0.243 - 108 -4.4577 2.5093 0.9155 1.1431 0.1002 0.5994 0.4556 0.0391 0.0000 0.0039 0.0976 0.241 - 109 -4.8128 2.3687 0.8353 1.1062 0.1006 0.6149 0.4674 0.0384 0.0000 0.0052 0.0991 0.239 - 110 -5.1540 2.2338 0.7518 1.0631 0.1020 0.6270 0.4766 0.0374 0.0000 0.0067 0.0998 0.236 - 111 -5.4774 2.1058 0.6671 1.0139 0.1043 0.6347 0.4824 0.0363 0.0000 0.0087 0.0993 0.232 - 112 -5.7795 1.9862 0.5830 0.9560 0.1075 0.6349 0.4826 0.0343 0.0000 0.0112 0.0972 0.227 - 113 -6.0570 1.8764 0.5012 0.8904 0.1116 0.6264 0.4761 0.0322 0.0000 0.0144 0.0931 0.220 - 114 -6.3069 1.7776 0.4225 0.8143 0.1163 0.6051 0.4599 0.0292 0.0000 0.0181 0.0864 0.211 - 115 -6.5264 1.6907 0.3478 0.7292 0.1212 0.5701 0.4333 0.0258 0.0000 0.0221 0.0771 0.199 - 116 -6.7314 1.6096 0.3326 0.6288 0.1262 0.5168 0.3928 0.0217 0.0000 0.0259 0.0649 0.184 - 117 -6.9144 1.5372 0.2507 0.5074 0.1310 0.4372 0.3323 0.0162 0.0000 0.0283 0.0496 0.165 + 91 -0.0047 4.2713 0.0803 1.6437 0.1677 0.4556 0.3464 0.2508 0.0000 -0.0162 0.0979 0.297 + 92 -0.0418 4.2566 0.2392 1.3494 0.1684 0.4097 0.3114 0.0590 0.0000 -0.0163 0.0837 0.302 + 93 -0.1156 4.2274 0.3930 1.3275 0.1686 0.4086 0.3106 0.0466 0.0000 -0.0154 0.0823 0.299 + 94 -0.2254 4.1839 0.5386 1.3209 0.1681 0.4116 0.3129 0.0434 0.0000 -0.0137 0.0813 0.294 + 95 -0.3698 4.1268 0.6730 1.3196 0.1666 0.4173 0.3172 0.0423 0.0000 -0.0117 0.0805 0.287 + 96 -0.5474 4.0565 0.7936 1.3167 0.1637 0.4239 0.3222 0.0415 0.0000 -0.0096 0.0798 0.280 + 97 -0.7617 3.9717 0.9441 1.3139 0.1592 0.4324 0.3287 0.0408 0.0000 -0.0076 0.0795 0.273 + 98 -1.0116 3.8728 1.0344 1.3073 0.1529 0.4416 0.3357 0.0397 0.0000 -0.0057 0.0795 0.267 + 99 -1.2891 3.7630 1.1046 1.3016 0.1448 0.4528 0.3442 0.0395 0.0000 -0.0041 0.0801 0.262 + 100 -1.5912 3.6435 1.1542 1.2937 0.1355 0.4651 0.3535 0.0393 0.0000 -0.0029 0.0810 0.258 + 101 -1.9146 3.5155 1.1831 1.2833 0.1263 0.4785 0.3637 0.0393 0.0000 -0.0018 0.0824 0.255 + 102 -2.2558 3.3805 1.1921 1.2705 0.1181 0.4928 0.3746 0.0394 0.0000 -0.0009 0.0840 0.253 + 103 -2.6109 3.2400 1.1821 1.2565 0.1118 0.5088 0.3867 0.0396 0.0000 -0.0002 0.0860 0.250 + 104 -2.9762 3.0955 1.1548 1.2404 0.1071 0.5260 0.3998 0.0398 0.0000 0.0006 0.0883 0.249 + 105 -3.3476 2.9485 1.1122 1.2210 0.1039 0.5439 0.4134 0.0397 0.0000 0.0013 0.0906 0.247 + 106 -3.7210 2.8008 1.0564 1.1980 0.1018 0.5622 0.4273 0.0396 0.0000 0.0020 0.0930 0.245 + 107 -4.0924 2.6538 0.9900 1.1716 0.1006 0.5806 0.4413 0.0393 0.0000 0.0029 0.0954 0.243 + 108 -4.4577 2.5093 0.9155 1.1412 0.1002 0.5984 0.4549 0.0389 0.0000 0.0039 0.0974 0.241 + 109 -4.8128 2.3687 0.8353 1.1047 0.1007 0.6141 0.4667 0.0383 0.0000 0.0052 0.0990 0.239 + 110 -5.1540 2.2338 0.7518 1.0621 0.1020 0.6265 0.4762 0.0374 0.0000 0.0067 0.0997 0.236 + 111 -5.4774 2.1058 0.6671 1.0125 0.1043 0.6339 0.4818 0.0361 0.0000 0.0087 0.0992 0.232 + 112 -5.7795 1.9862 0.5830 0.9548 0.1076 0.6342 0.4821 0.0340 0.0000 0.0112 0.0971 0.227 + 113 -6.0570 1.8764 0.5012 0.8896 0.1116 0.6258 0.4756 0.0322 0.0000 0.0144 0.0930 0.220 + 114 -6.3069 1.7776 0.4225 0.8142 0.1163 0.6050 0.4598 0.0295 0.0000 0.0181 0.0863 0.211 + 115 -6.5264 1.6907 0.3478 0.7291 0.1212 0.5700 0.4333 0.0258 0.0000 0.0221 0.0771 0.199 + 116 -6.7314 1.6096 0.3326 0.6288 0.1262 0.5168 0.3928 0.0216 0.0000 0.0259 0.0649 0.184 + 117 -6.9144 1.5372 0.2507 0.5068 0.1311 0.4367 0.3319 0.0161 0.0000 0.0282 0.0496 0.165 118 -7.0535 1.4822 0.1746 0.3720 0.1349 0.3330 0.2531 0.0100 0.0000 0.0266 0.0334 0.145 119 -7.1471 1.4451 0.1029 0.2273 0.1376 0.2092 0.1590 0.0042 0.0000 0.0196 0.0186 0.127 - 120 -7.1941 1.4265 0.0340 0.0766 0.1391 0.0721 0.0548 -0.0017 0.0000 0.0073 0.0059 0.118 + 120 -7.1941 1.4265 0.0340 0.0766 0.1391 0.0721 0.0548 -0.0017 0.0000 0.0073 0.0059 0.117 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.372 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.379 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.391 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.404 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.407 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.408 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.402 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.386 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.358 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.317 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.276 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.267 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.260 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.255 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.246 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.245 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.203 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.189 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.176 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.157 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.134 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.108 + 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.338 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.346 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.344 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.360 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.360 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.362 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.362 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.345 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.325 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.289 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.246 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.212 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.200 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.188 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.170 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.152 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.130 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.110 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.101 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01753 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.09562 + CLsurf = 0.01746 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = 0.09569 CDsurf = -0.00020 Cnsurf = -0.00000 CDisurf = -0.00020 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01767 CDsurf = -0.00020 + CLsurf = 0.01760 CDsurf = -0.00021 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.4049 0.2572 0.1531 0.0164 -0.0053 0.0000 0.0063 0.0003 -0.137 - 152 -1.3090 31.2096 11.6724 0.5633 0.2727 0.0667 0.0186 -0.0016 0.0000 0.0081 0.0009 -0.186 - 153 -0.9350 34.0626 12.7394 0.6127 0.2464 0.0428 0.0183 -0.0001 0.0000 0.0099 0.0018 -0.291 - 154 -0.5610 36.1619 13.5246 0.6395 0.2360 0.0292 0.0178 0.0011 0.0000 0.0108 0.0028 -0.356 - 155 -0.1870 37.5332 14.0374 0.6551 0.2345 0.0198 0.0172 0.0032 0.0000 0.0110 0.0046 -0.389 - 156 0.1870 37.5332 14.0374 0.6551 0.2345 0.0198 0.0172 0.0032 0.0000 0.0110 0.0046 -0.389 - 157 0.5610 36.1619 13.5246 0.6395 0.2360 0.0292 0.0178 0.0011 0.0000 0.0108 0.0028 -0.356 - 158 0.9350 34.0626 12.7394 0.6127 0.2464 0.0428 0.0183 -0.0001 0.0000 0.0099 0.0018 -0.291 - 159 1.3090 31.2096 11.6724 0.5633 0.2727 0.0667 0.0186 -0.0016 0.0000 0.0081 0.0009 -0.186 - 160 1.6830 26.5957 9.9468 0.4049 0.2572 0.1531 0.0164 -0.0053 0.0000 0.0063 0.0003 -0.137 + 151 -1.6830 26.5957 9.9468 0.4032 0.2571 0.1525 0.0163 -0.0053 0.0000 0.0064 0.0003 -0.140 + 152 -1.3090 31.2096 11.6724 0.5610 0.2727 0.0665 0.0185 -0.0016 0.0000 0.0081 0.0009 -0.189 + 153 -0.9350 34.0626 12.7394 0.6102 0.2466 0.0427 0.0182 -0.0001 0.0000 0.0099 0.0018 -0.295 + 154 -0.5610 36.1619 13.5246 0.6370 0.2362 0.0291 0.0177 0.0011 0.0000 0.0108 0.0028 -0.359 + 155 -0.1870 37.5332 14.0374 0.6526 0.2347 0.0198 0.0171 0.0032 0.0000 0.0110 0.0046 -0.393 + 156 0.1870 37.5332 14.0374 0.6526 0.2347 0.0198 0.0171 0.0032 0.0000 0.0110 0.0046 -0.393 + 157 0.5610 36.1619 13.5246 0.6370 0.2362 0.0291 0.0177 0.0011 0.0000 0.0108 0.0028 -0.359 + 158 0.9350 34.0626 12.7394 0.6102 0.2466 0.0427 0.0182 -0.0001 0.0000 0.0099 0.0018 -0.295 + 159 1.3090 31.2096 11.6724 0.5610 0.2727 0.0665 0.0185 -0.0016 0.0000 0.0081 0.0009 -0.189 + 160 1.6830 26.5957 9.9468 0.4032 0.2571 0.1525 0.0163 -0.0053 0.0000 0.0064 0.0003 -0.140 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = -0.00000 Clsurf = -0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = 0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.646 - 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0003 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.920 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.189 - 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.401 - 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.517 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.607 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.684 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.780 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 1.596 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.885 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.248 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.088 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.509 + 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.606 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.656 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.711 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.789 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_02_01.txt b/regression/scripts/AVL/avl_files/strip_forces_case_02_01.txt index aefc28ff2e..ad336571f5 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_02_01.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_02_01.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00865 Clsurf = 0.00261 - CYsurf = 0.00014 Cmsurf = 0.00393 - CDsurf = 0.00038 Cnsurf = -0.00020 + CLsurf = 0.00926 Clsurf = 0.00255 + CYsurf = 0.00012 Cmsurf = 0.00360 + CDsurf = 0.00038 Cnsurf = -0.00019 CDisurf = 0.00038 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01683 CDsurf = 0.00074 + CLsurf = 0.01802 CDsurf = 0.00075 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 0.7142 0.0123 0.1194 0.0928 0.0172 0.0000 -0.0042 -0.0221 0.295 - 2 0.1025 7.6885 1.0492 0.7030 0.0115 0.1179 0.0917 0.0044 0.0000 -0.0042 -0.0220 0.296 - 3 0.2837 7.5620 1.7073 0.6986 0.0098 0.1191 0.0926 0.0035 0.0000 -0.0039 -0.0219 0.292 - 4 0.5530 7.3741 2.3052 0.6880 0.0074 0.1203 0.0935 0.0030 0.0000 -0.0035 -0.0218 0.288 - 5 0.9075 7.1267 2.8223 0.6668 0.0050 0.1206 0.0937 0.0025 0.0000 -0.0033 -0.0217 0.285 - 6 1.3432 6.8226 3.2414 0.6312 0.0058 0.1192 0.0926 0.0019 0.0000 -0.0033 -0.0215 0.286 - 7 1.8554 6.4651 3.5491 0.5779 0.0155 0.1152 0.0895 0.0014 0.0000 -0.0037 -0.0212 0.291 - 8 2.4386 6.0582 3.7368 0.5051 0.0230 0.1074 0.0834 0.0007 0.0000 -0.0045 -0.0206 0.304 - 9 3.0862 5.6062 3.8005 0.4131 0.0156 0.0949 0.0737 0.0002 0.0000 -0.0059 -0.0198 0.330 - 10 3.7613 5.1351 3.4440 0.3120 0.0058 0.0782 0.0608 -0.0001 0.0000 -0.0081 -0.0190 0.384 - 11 4.4532 4.6522 3.3149 0.2075 -0.0026 0.0574 0.0446 -0.0003 0.0000 -0.0113 -0.0183 0.504 - 12 5.1831 4.1429 3.0930 0.1002 -0.0129 0.0311 0.0242 -0.0003 0.0000 -0.0158 -0.0178 0.904 - 13 6.0123 3.7903 3.4706 0.0080 -0.0178 0.0026 0.0021 -0.0001 0.0000 -0.0196 -0.0179 - 14 6.9353 3.6075 3.3775 -0.0520 -0.0136 -0.0175 -0.0144 0.0001 0.0000 -0.0202 -0.0148 - 15 7.8737 3.4215 3.2389 -0.0937 -0.0101 -0.0332 -0.0274 0.0002 0.0000 -0.0204 -0.0121 -0.493 - 16 8.8172 3.2345 3.0619 -0.1224 -0.0077 -0.0459 -0.0379 0.0003 0.0000 -0.0204 -0.0098 -0.288 - 17 9.7556 3.0486 2.8543 -0.1415 -0.0065 -0.0563 -0.0464 0.0003 0.0000 -0.0204 -0.0079 -0.189 - 18 10.6786 2.8657 2.6240 -0.1531 -0.0060 -0.0649 -0.0534 0.0003 0.0000 -0.0203 -0.0063 -0.131 - 19 11.5760 2.6879 2.3787 -0.1589 -0.0058 -0.0718 -0.0591 0.0003 0.0000 -0.0204 -0.0051 -0.094 - 20 12.4328 2.5181 2.1010 -0.1601 -0.0059 -0.0772 -0.0636 0.0002 0.0000 -0.0204 -0.0041 -0.071 - 21 13.2400 2.3582 1.8520 -0.1575 -0.0061 -0.0811 -0.0668 0.0002 0.0000 -0.0205 -0.0035 -0.056 - 22 13.9941 2.2087 1.6074 -0.1517 -0.0064 -0.0834 -0.0687 0.0002 0.0000 -0.0206 -0.0032 -0.050 - 23 14.6868 2.0715 1.3716 -0.1429 -0.0070 -0.0838 -0.0690 0.0002 0.0000 -0.0208 -0.0033 -0.052 - 24 15.3105 1.9479 1.1479 -0.1306 -0.0075 -0.0815 -0.0671 0.0001 0.0000 -0.0211 -0.0040 -0.065 - 25 15.8583 1.8393 0.9381 -0.1147 -0.0079 -0.0757 -0.0624 0.0001 0.0000 -0.0211 -0.0050 -0.088 - 26 16.3244 1.7470 0.7427 -0.0951 -0.0079 -0.0661 -0.0545 0.0001 0.0000 -0.0194 -0.0052 -0.106 - 27 16.6722 1.4928 0.4131 -0.0738 -0.0077 -0.1631 -0.0495 -0.0006 0.0000 -0.0152 -0.0015 -0.057 - 28 16.9098 1.1466 0.2292 -0.0522 -0.0064 -0.1503 -0.0456 -0.0009 0.0000 -0.0162 -0.0024 -0.105 - 29 17.0696 0.9138 0.1104 -0.0307 -0.0045 -0.1108 -0.0336 -0.0013 0.0000 -0.0151 -0.0033 -0.199 - 30 17.1499 0.7967 0.0322 -0.0101 -0.0034 -0.0419 -0.0127 -0.0022 0.0000 -0.0072 -0.0019 -0.317 + 1 0.0114 7.7520 0.3539 0.7298 0.0122 0.1220 0.0948 0.0170 0.0000 -0.0055 -0.0236 0.308 + 2 0.1025 7.6885 1.0491 0.7183 0.0115 0.1205 0.0936 0.0044 0.0000 -0.0055 -0.0234 0.308 + 3 0.2837 7.5620 1.7073 0.7140 0.0101 0.1217 0.0946 0.0035 0.0000 -0.0052 -0.0234 0.305 + 4 0.5530 7.3741 2.3052 0.7036 0.0079 0.1230 0.0956 0.0029 0.0000 -0.0048 -0.0233 0.301 + 5 0.9075 7.1267 2.8223 0.6825 0.0056 0.1234 0.0959 0.0025 0.0000 -0.0046 -0.0232 0.298 + 6 1.3432 6.8226 3.2414 0.6466 0.0064 0.1221 0.0949 0.0020 0.0000 -0.0046 -0.0230 0.298 + 7 1.8554 6.4651 3.5491 0.5926 0.0162 0.1181 0.0918 0.0013 0.0000 -0.0048 -0.0226 0.303 + 8 2.4386 6.0582 3.7368 0.5189 0.0236 0.1103 0.0857 0.0008 0.0000 -0.0055 -0.0219 0.314 + 9 3.0862 5.6062 3.8005 0.4261 0.0164 0.0979 0.0761 0.0003 0.0000 -0.0068 -0.0210 0.339 + 10 3.7613 5.1351 3.4440 0.3218 0.0064 0.0807 0.0627 -0.0001 0.0000 -0.0086 -0.0198 0.388 + 11 4.4532 4.6522 3.3149 0.2146 -0.0027 0.0594 0.0461 -0.0003 0.0000 -0.0112 -0.0185 0.492 + 12 5.1831 4.1429 3.0930 0.1040 -0.0135 0.0323 0.0251 -0.0003 0.0000 -0.0149 -0.0172 0.842 + 13 6.0123 3.7903 3.4706 0.0105 -0.0182 0.0033 0.0028 -0.0001 0.0000 -0.0181 -0.0167 + 14 6.9353 3.6075 3.3775 -0.0499 -0.0139 -0.0168 -0.0139 0.0001 0.0000 -0.0187 -0.0136 + 15 7.8737 3.4215 3.2389 -0.0919 -0.0102 -0.0326 -0.0269 0.0002 0.0000 -0.0188 -0.0108 -0.449 + 16 8.8172 3.2345 3.0619 -0.1209 -0.0078 -0.0454 -0.0374 0.0003 0.0000 -0.0188 -0.0085 -0.252 + 17 9.7556 3.0486 2.8543 -0.1402 -0.0065 -0.0558 -0.0460 0.0003 0.0000 -0.0188 -0.0065 -0.158 + 18 10.6786 2.8657 2.6239 -0.1520 -0.0060 -0.0644 -0.0531 0.0003 0.0000 -0.0187 -0.0050 -0.103 + 19 11.5760 2.6879 2.3787 -0.1580 -0.0059 -0.0714 -0.0588 0.0003 0.0000 -0.0187 -0.0037 -0.069 + 20 12.4328 2.5181 2.1010 -0.1593 -0.0059 -0.0768 -0.0633 0.0003 0.0000 -0.0188 -0.0027 -0.047 + 21 13.2400 2.3582 1.8520 -0.1569 -0.0061 -0.0808 -0.0666 0.0002 0.0000 -0.0189 -0.0021 -0.033 + 22 13.9941 2.2087 1.6074 -0.1512 -0.0065 -0.0832 -0.0685 0.0002 0.0000 -0.0190 -0.0018 -0.027 + 23 14.6868 2.0715 1.3716 -0.1425 -0.0070 -0.0836 -0.0688 0.0002 0.0000 -0.0192 -0.0019 -0.029 + 24 15.3105 1.9479 1.1479 -0.1305 -0.0075 -0.0814 -0.0670 0.0001 0.0000 -0.0195 -0.0026 -0.041 + 25 15.8583 1.8393 0.9381 -0.1148 -0.0079 -0.0758 -0.0624 0.0001 0.0000 -0.0195 -0.0035 -0.062 + 26 16.3244 1.7470 0.7427 -0.0955 -0.0082 -0.0664 -0.0547 0.0001 0.0000 -0.0178 -0.0038 -0.076 + 27 16.6722 1.4928 0.4131 -0.0743 -0.0080 -0.1641 -0.0498 -0.0005 0.0000 -0.0139 -0.0008 -0.030 + 28 16.9098 1.1466 0.2292 -0.0524 -0.0065 -0.1507 -0.0457 -0.0009 0.0000 -0.0152 -0.0019 -0.082 + 29 17.0696 0.9138 0.1104 -0.0307 -0.0043 -0.1108 -0.0336 -0.0013 0.0000 -0.0145 -0.0030 -0.181 + 30 17.1499 0.7967 0.0322 -0.0100 -0.0027 -0.0417 -0.0126 -0.0021 0.0000 -0.0070 -0.0019 -0.307 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00865 Clsurf = -0.00261 - CYsurf = -0.00014 Cmsurf = 0.00393 - CDsurf = 0.00038 Cnsurf = 0.00020 + CLsurf = 0.00926 Clsurf = -0.00255 + CYsurf = -0.00012 Cmsurf = 0.00360 + CDsurf = 0.00038 Cnsurf = 0.00019 CDisurf = 0.00038 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01683 CDsurf = 0.00074 + CLsurf = 0.01802 CDsurf = 0.00075 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 0.7142 0.0122 0.1194 0.0928 0.0172 0.0000 -0.0042 0.0221 0.295 - 32 -0.1025 7.6885 1.0492 0.7030 0.0115 0.1179 0.0916 0.0044 0.0000 -0.0042 0.0220 0.296 - 33 -0.2837 7.5620 1.7073 0.6985 0.0098 0.1191 0.0926 0.0035 0.0000 -0.0039 0.0219 0.292 - 34 -0.5530 7.3741 2.3052 0.6880 0.0074 0.1203 0.0935 0.0030 0.0000 -0.0035 0.0218 0.288 - 35 -0.9075 7.1267 2.8223 0.6668 0.0050 0.1206 0.0937 0.0025 0.0000 -0.0033 0.0217 0.285 - 36 -1.3432 6.8226 3.2414 0.6312 0.0058 0.1192 0.0926 0.0019 0.0000 -0.0033 0.0215 0.286 - 37 -1.8554 6.4651 3.5491 0.5779 0.0155 0.1152 0.0895 0.0014 0.0000 -0.0037 0.0212 0.291 - 38 -2.4386 6.0582 3.7368 0.5051 0.0230 0.1074 0.0834 0.0007 0.0000 -0.0045 0.0206 0.304 - 39 -3.0862 5.6062 3.8005 0.4131 0.0156 0.0949 0.0737 0.0002 0.0000 -0.0059 0.0198 0.330 - 40 -3.7613 5.1351 3.4440 0.3120 0.0058 0.0782 0.0608 -0.0001 0.0000 -0.0081 0.0190 0.384 - 41 -4.4532 4.6522 3.3149 0.2075 -0.0026 0.0574 0.0446 -0.0003 0.0000 -0.0113 0.0183 0.504 - 42 -5.1831 4.1429 3.0930 0.1002 -0.0129 0.0311 0.0242 -0.0003 0.0000 -0.0158 0.0178 0.904 - 43 -6.0123 3.7903 3.4706 0.0080 -0.0178 0.0026 0.0021 -0.0001 0.0000 -0.0196 0.0179 - 44 -6.9353 3.6075 3.3775 -0.0520 -0.0136 -0.0175 -0.0144 0.0001 0.0000 -0.0202 0.0148 - 45 -7.8737 3.4215 3.2389 -0.0937 -0.0101 -0.0332 -0.0274 0.0002 0.0000 -0.0204 0.0121 -0.493 - 46 -8.8172 3.2345 3.0619 -0.1224 -0.0077 -0.0459 -0.0379 0.0003 0.0000 -0.0204 0.0098 -0.288 - 47 -9.7556 3.0486 2.8543 -0.1415 -0.0065 -0.0563 -0.0464 0.0003 0.0000 -0.0204 0.0079 -0.189 - 48 -10.6786 2.8657 2.6240 -0.1531 -0.0060 -0.0649 -0.0534 0.0003 0.0000 -0.0203 0.0063 -0.131 - 49 -11.5760 2.6879 2.3787 -0.1589 -0.0058 -0.0718 -0.0591 0.0003 0.0000 -0.0204 0.0051 -0.094 - 50 -12.4328 2.5181 2.1010 -0.1601 -0.0059 -0.0772 -0.0636 0.0002 0.0000 -0.0204 0.0041 -0.071 - 51 -13.2400 2.3582 1.8520 -0.1575 -0.0061 -0.0811 -0.0668 0.0002 0.0000 -0.0205 0.0035 -0.056 - 52 -13.9941 2.2087 1.6074 -0.1517 -0.0064 -0.0834 -0.0687 0.0002 0.0000 -0.0206 0.0032 -0.050 - 53 -14.6868 2.0715 1.3716 -0.1429 -0.0070 -0.0838 -0.0690 0.0002 0.0000 -0.0208 0.0033 -0.052 - 54 -15.3105 1.9479 1.1479 -0.1306 -0.0075 -0.0815 -0.0671 0.0001 0.0000 -0.0211 0.0040 -0.065 - 55 -15.8583 1.8393 0.9381 -0.1147 -0.0079 -0.0757 -0.0624 0.0001 0.0000 -0.0211 0.0050 -0.088 - 56 -16.3244 1.7470 0.7427 -0.0951 -0.0079 -0.0661 -0.0545 0.0001 0.0000 -0.0194 0.0052 -0.106 - 57 -16.6722 1.4928 0.4131 -0.0738 -0.0077 -0.1631 -0.0495 -0.0006 0.0000 -0.0152 0.0015 -0.057 - 58 -16.9098 1.1466 0.2292 -0.0522 -0.0064 -0.1503 -0.0456 -0.0009 0.0000 -0.0162 0.0024 -0.105 - 59 -17.0696 0.9138 0.1104 -0.0307 -0.0045 -0.1108 -0.0336 -0.0013 0.0000 -0.0151 0.0033 -0.199 - 60 -17.1499 0.7967 0.0322 -0.0101 -0.0034 -0.0419 -0.0127 -0.0022 0.0000 -0.0072 0.0019 -0.317 + 31 -0.0114 7.7520 0.3539 0.7298 0.0122 0.1220 0.0948 0.0170 0.0000 -0.0055 0.0236 0.308 + 32 -0.1025 7.6885 1.0491 0.7183 0.0115 0.1205 0.0936 0.0044 0.0000 -0.0055 0.0234 0.308 + 33 -0.2837 7.5620 1.7073 0.7140 0.0101 0.1217 0.0946 0.0035 0.0000 -0.0052 0.0234 0.305 + 34 -0.5530 7.3741 2.3052 0.7036 0.0079 0.1230 0.0956 0.0029 0.0000 -0.0048 0.0233 0.301 + 35 -0.9075 7.1267 2.8223 0.6825 0.0056 0.1234 0.0959 0.0025 0.0000 -0.0046 0.0232 0.298 + 36 -1.3432 6.8226 3.2414 0.6466 0.0064 0.1221 0.0949 0.0020 0.0000 -0.0046 0.0230 0.298 + 37 -1.8554 6.4651 3.5491 0.5926 0.0162 0.1181 0.0918 0.0013 0.0000 -0.0048 0.0226 0.303 + 38 -2.4386 6.0582 3.7368 0.5189 0.0236 0.1103 0.0857 0.0008 0.0000 -0.0055 0.0219 0.314 + 39 -3.0862 5.6062 3.8005 0.4261 0.0164 0.0979 0.0761 0.0003 0.0000 -0.0068 0.0210 0.339 + 40 -3.7613 5.1351 3.4440 0.3218 0.0064 0.0807 0.0627 -0.0001 0.0000 -0.0086 0.0198 0.388 + 41 -4.4532 4.6522 3.3149 0.2146 -0.0027 0.0594 0.0461 -0.0003 0.0000 -0.0112 0.0185 0.492 + 42 -5.1831 4.1429 3.0930 0.1040 -0.0135 0.0323 0.0251 -0.0003 0.0000 -0.0149 0.0172 0.842 + 43 -6.0123 3.7903 3.4706 0.0105 -0.0182 0.0033 0.0028 -0.0001 0.0000 -0.0181 0.0167 + 44 -6.9353 3.6075 3.3775 -0.0499 -0.0139 -0.0168 -0.0139 0.0001 0.0000 -0.0187 0.0136 + 45 -7.8737 3.4215 3.2389 -0.0919 -0.0102 -0.0326 -0.0269 0.0002 0.0000 -0.0188 0.0108 -0.449 + 46 -8.8172 3.2345 3.0619 -0.1209 -0.0078 -0.0454 -0.0374 0.0003 0.0000 -0.0188 0.0085 -0.252 + 47 -9.7556 3.0486 2.8543 -0.1402 -0.0065 -0.0558 -0.0460 0.0003 0.0000 -0.0188 0.0065 -0.158 + 48 -10.6786 2.8657 2.6239 -0.1520 -0.0060 -0.0644 -0.0531 0.0003 0.0000 -0.0187 0.0050 -0.103 + 49 -11.5760 2.6879 2.3787 -0.1580 -0.0059 -0.0714 -0.0588 0.0003 0.0000 -0.0187 0.0037 -0.069 + 50 -12.4328 2.5181 2.1010 -0.1593 -0.0059 -0.0768 -0.0633 0.0003 0.0000 -0.0188 0.0027 -0.047 + 51 -13.2400 2.3582 1.8520 -0.1569 -0.0061 -0.0808 -0.0666 0.0002 0.0000 -0.0189 0.0021 -0.033 + 52 -13.9941 2.2087 1.6074 -0.1512 -0.0065 -0.0832 -0.0685 0.0002 0.0000 -0.0190 0.0018 -0.027 + 53 -14.6868 2.0715 1.3716 -0.1425 -0.0070 -0.0836 -0.0688 0.0002 0.0000 -0.0192 0.0019 -0.029 + 54 -15.3105 1.9479 1.1479 -0.1305 -0.0075 -0.0814 -0.0670 0.0001 0.0000 -0.0195 0.0026 -0.041 + 55 -15.8583 1.8393 0.9381 -0.1148 -0.0079 -0.0758 -0.0624 0.0001 0.0000 -0.0195 0.0035 -0.062 + 56 -16.3244 1.7470 0.7427 -0.0955 -0.0082 -0.0664 -0.0547 0.0001 0.0000 -0.0178 0.0038 -0.076 + 57 -16.6722 1.4928 0.4131 -0.0743 -0.0080 -0.1641 -0.0498 -0.0005 0.0000 -0.0139 0.0008 -0.030 + 58 -16.9098 1.1466 0.2292 -0.0524 -0.0065 -0.1507 -0.0457 -0.0009 0.0000 -0.0152 0.0019 -0.082 + 59 -17.0696 0.9138 0.1104 -0.0307 -0.0043 -0.1108 -0.0336 -0.0013 0.0000 -0.0145 0.0030 -0.181 + 60 -17.1499 0.7967 0.0322 -0.0100 -0.0027 -0.0417 -0.0126 -0.0021 0.0000 -0.0070 0.0019 -0.307 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02792 Clsurf = 0.00272 - CYsurf = 0.00449 Cmsurf = 0.13390 - CDsurf = 0.00011 Cnsurf = -0.00277 - CDisurf = 0.00011 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02806 Clsurf = 0.00273 + CYsurf = 0.00452 Cmsurf = 0.13455 + CDsurf = 0.00010 Cnsurf = -0.00278 + CDisurf = 0.00010 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.17021 CDsurf = 0.00066 + CLsurf = -0.17106 CDsurf = 0.00063 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.5754 -0.0207 -0.1705 -0.1330 0.0535 0.0000 0.0080 0.0349 0.310 - 62 0.0418 4.2566 0.2392 -0.6506 -0.0211 -0.1958 -0.1527 0.0064 0.0000 0.0076 0.0383 0.299 - 63 0.1156 4.2274 0.3930 -0.6562 -0.0216 -0.1990 -0.1552 0.0034 0.0000 0.0071 0.0384 0.296 - 64 0.2254 4.1839 0.5386 -0.6579 -0.0218 -0.2016 -0.1573 0.0026 0.0000 0.0062 0.0381 0.290 - 65 0.3698 4.1268 0.6730 -0.6579 -0.0218 -0.2044 -0.1595 0.0022 0.0000 0.0052 0.0377 0.283 - 66 0.5474 4.0565 0.7936 -0.6572 -0.0215 -0.2078 -0.1620 0.0017 0.0000 0.0042 0.0374 0.276 - 67 0.7617 3.9717 0.9441 -0.6553 -0.0208 -0.2116 -0.1650 0.0014 0.0000 0.0031 0.0371 0.269 - 68 1.0116 3.8728 1.0344 -0.6510 -0.0194 -0.2156 -0.1682 0.0010 0.0000 0.0022 0.0370 0.263 - 69 1.2891 3.7630 1.1046 -0.6448 -0.0174 -0.2198 -0.1714 0.0007 0.0000 0.0014 0.0370 0.258 - 70 1.5912 3.6435 1.1542 -0.6354 -0.0150 -0.2237 -0.1745 0.0005 0.0000 0.0008 0.0371 0.254 - 71 1.9146 3.5155 1.1831 -0.6229 -0.0125 -0.2273 -0.1773 0.0003 0.0000 0.0003 0.0373 0.252 - 72 2.2558 3.3805 1.1921 -0.6075 -0.0106 -0.2306 -0.1798 0.0001 0.0000 -0.0001 0.0374 0.249 - 73 2.6109 3.2400 1.1821 -0.5885 -0.0095 -0.2330 -0.1817 -0.0000 0.0000 -0.0004 0.0376 0.248 - 74 2.9762 3.0955 1.1548 -0.5667 -0.0091 -0.2349 -0.1832 -0.0001 0.0000 -0.0006 0.0377 0.247 - 75 3.3476 2.9485 1.1122 -0.5422 -0.0093 -0.2359 -0.1840 -0.0002 0.0000 -0.0007 0.0378 0.246 - 76 3.7210 2.8008 1.0564 -0.5154 -0.0098 -0.2361 -0.1841 -0.0002 0.0000 -0.0009 0.0377 0.245 - 77 4.0924 2.6538 0.9900 -0.4872 -0.0104 -0.2356 -0.1837 -0.0002 0.0000 -0.0010 0.0375 0.245 - 78 4.4577 2.5093 0.9155 -0.4578 -0.0112 -0.2341 -0.1826 -0.0002 0.0000 -0.0012 0.0371 0.244 - 79 4.8128 2.3687 0.8353 -0.4279 -0.0121 -0.2318 -0.1808 -0.0002 0.0000 -0.0014 0.0365 0.242 - 80 5.1540 2.2338 0.7518 -0.3976 -0.0131 -0.2284 -0.1781 -0.0001 0.0000 -0.0017 0.0357 0.240 - 81 5.4774 2.1058 0.6671 -0.3669 -0.0143 -0.2235 -0.1743 -0.0001 0.0000 -0.0022 0.0345 0.237 - 82 5.7795 1.9862 0.5830 -0.3361 -0.0157 -0.2171 -0.1693 -0.0002 0.0000 -0.0029 0.0329 0.233 - 83 6.0570 1.8764 0.5012 -0.3047 -0.0172 -0.2083 -0.1625 -0.0002 0.0000 -0.0037 0.0307 0.227 - 84 6.3069 1.7776 0.4225 -0.2726 -0.0189 -0.1968 -0.1534 -0.0002 0.0000 -0.0048 0.0280 0.219 - 85 6.5264 1.6907 0.3478 -0.2392 -0.0205 -0.1815 -0.1416 -0.0003 0.0000 -0.0060 0.0245 0.208 - 86 6.7314 1.6096 0.3326 -0.2024 -0.0222 -0.1614 -0.1259 -0.0003 0.0000 -0.0071 0.0202 0.193 - 87 6.9144 1.5372 0.2507 -0.1609 -0.0238 -0.1343 -0.1048 -0.0004 0.0000 -0.0079 0.0152 0.175 - 88 7.0535 1.4822 0.1746 -0.1168 -0.0250 -0.1012 -0.0789 -0.0005 0.0000 -0.0075 0.0101 0.155 - 89 7.1471 1.4451 0.1029 -0.0709 -0.0259 -0.0630 -0.0491 -0.0005 0.0000 -0.0055 0.0056 0.138 - 90 7.1941 1.4265 0.0340 -0.0238 -0.0264 -0.0214 -0.0167 -0.0005 0.0000 -0.0020 0.0017 0.127 + 61 0.0047 4.2713 0.0803 -0.5783 -0.0206 -0.1713 -0.1336 0.0541 0.0000 0.0080 0.0350 0.310 + 62 0.0418 4.2566 0.2392 -0.6544 -0.0210 -0.1970 -0.1536 0.0065 0.0000 0.0076 0.0385 0.299 + 63 0.1156 4.2274 0.3930 -0.6603 -0.0215 -0.2002 -0.1562 0.0034 0.0000 0.0071 0.0386 0.295 + 64 0.2254 4.1839 0.5386 -0.6619 -0.0217 -0.2028 -0.1582 0.0026 0.0000 0.0063 0.0383 0.290 + 65 0.3698 4.1268 0.6730 -0.6620 -0.0217 -0.2057 -0.1604 0.0021 0.0000 0.0052 0.0379 0.283 + 66 0.5474 4.0565 0.7936 -0.6614 -0.0214 -0.2091 -0.1631 0.0018 0.0000 0.0042 0.0376 0.276 + 67 0.7617 3.9717 0.9441 -0.6591 -0.0207 -0.2129 -0.1660 0.0014 0.0000 0.0031 0.0373 0.269 + 68 1.0116 3.8728 1.0344 -0.6554 -0.0193 -0.2171 -0.1693 0.0010 0.0000 0.0022 0.0372 0.263 + 69 1.2891 3.7630 1.1046 -0.6486 -0.0173 -0.2211 -0.1724 0.0007 0.0000 0.0014 0.0372 0.258 + 70 1.5912 3.6435 1.1542 -0.6392 -0.0149 -0.2251 -0.1755 0.0004 0.0000 0.0008 0.0373 0.254 + 71 1.9146 3.5155 1.1831 -0.6267 -0.0124 -0.2287 -0.1784 0.0002 0.0000 0.0003 0.0375 0.252 + 72 2.2558 3.3805 1.1921 -0.6110 -0.0105 -0.2319 -0.1809 0.0001 0.0000 -0.0001 0.0377 0.249 + 73 2.6109 3.2400 1.1821 -0.5918 -0.0094 -0.2344 -0.1828 -0.0000 0.0000 -0.0004 0.0378 0.248 + 74 2.9762 3.0955 1.1548 -0.5696 -0.0090 -0.2361 -0.1841 -0.0001 0.0000 -0.0006 0.0379 0.247 + 75 3.3476 2.9485 1.1122 -0.5449 -0.0092 -0.2371 -0.1849 -0.0002 0.0000 -0.0008 0.0380 0.246 + 76 3.7210 2.8008 1.0564 -0.5180 -0.0097 -0.2373 -0.1851 -0.0002 0.0000 -0.0009 0.0379 0.245 + 77 4.0924 2.6538 0.9900 -0.4894 -0.0103 -0.2366 -0.1846 -0.0002 0.0000 -0.0010 0.0377 0.244 + 78 4.4577 2.5093 0.9155 -0.4598 -0.0111 -0.2351 -0.1833 -0.0002 0.0000 -0.0012 0.0373 0.244 + 79 4.8128 2.3687 0.8353 -0.4295 -0.0120 -0.2326 -0.1814 -0.0002 0.0000 -0.0014 0.0367 0.242 + 80 5.1540 2.2338 0.7518 -0.3989 -0.0131 -0.2291 -0.1787 -0.0002 0.0000 -0.0017 0.0358 0.240 + 81 5.4774 2.1058 0.6671 -0.3680 -0.0143 -0.2242 -0.1749 -0.0001 0.0000 -0.0022 0.0346 0.237 + 82 5.7795 1.9862 0.5830 -0.3371 -0.0156 -0.2178 -0.1698 -0.0002 0.0000 -0.0029 0.0330 0.233 + 83 6.0570 1.8764 0.5012 -0.3054 -0.0172 -0.2089 -0.1629 -0.0002 0.0000 -0.0037 0.0308 0.227 + 84 6.3069 1.7776 0.4225 -0.2731 -0.0189 -0.1972 -0.1538 -0.0002 0.0000 -0.0048 0.0280 0.219 + 85 6.5264 1.6907 0.3478 -0.2396 -0.0205 -0.1819 -0.1418 -0.0003 0.0000 -0.0060 0.0245 0.208 + 86 6.7314 1.6096 0.3326 -0.2028 -0.0222 -0.1617 -0.1261 -0.0004 0.0000 -0.0071 0.0203 0.194 + 87 6.9144 1.5372 0.2507 -0.1612 -0.0238 -0.1346 -0.1050 -0.0004 0.0000 -0.0079 0.0152 0.175 + 88 7.0535 1.4822 0.1746 -0.1170 -0.0250 -0.1013 -0.0790 -0.0005 0.0000 -0.0075 0.0102 0.155 + 89 7.1471 1.4451 0.1029 -0.0710 -0.0259 -0.0631 -0.0492 -0.0005 0.0000 -0.0055 0.0056 0.138 + 90 7.1941 1.4265 0.0340 -0.0238 -0.0264 -0.0214 -0.0167 -0.0005 0.0000 -0.0020 0.0018 0.127 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02792 Clsurf = -0.00272 - CYsurf = -0.00449 Cmsurf = 0.13389 - CDsurf = 0.00011 Cnsurf = 0.00277 - CDisurf = 0.00011 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02806 Clsurf = -0.00273 + CYsurf = -0.00452 Cmsurf = 0.13455 + CDsurf = 0.00010 Cnsurf = 0.00278 + CDisurf = 0.00010 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.17020 CDsurf = 0.00066 + CLsurf = -0.17106 CDsurf = 0.00063 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.5754 -0.0207 -0.1705 -0.1330 0.0535 0.0000 0.0080 -0.0349 0.310 - 92 -0.0418 4.2566 0.2392 -0.6506 -0.0211 -0.1958 -0.1527 0.0064 0.0000 0.0076 -0.0383 0.299 - 93 -0.1156 4.2274 0.3930 -0.6562 -0.0216 -0.1990 -0.1552 0.0034 0.0000 0.0071 -0.0384 0.296 - 94 -0.2254 4.1839 0.5386 -0.6579 -0.0218 -0.2016 -0.1573 0.0026 0.0000 0.0062 -0.0381 0.290 - 95 -0.3698 4.1268 0.6730 -0.6579 -0.0218 -0.2044 -0.1594 0.0022 0.0000 0.0052 -0.0377 0.283 - 96 -0.5474 4.0565 0.7936 -0.6572 -0.0215 -0.2078 -0.1620 0.0017 0.0000 0.0042 -0.0374 0.276 - 97 -0.7617 3.9717 0.9441 -0.6553 -0.0208 -0.2116 -0.1650 0.0014 0.0000 0.0031 -0.0371 0.269 - 98 -1.0116 3.8728 1.0344 -0.6510 -0.0194 -0.2156 -0.1682 0.0010 0.0000 0.0022 -0.0370 0.263 - 99 -1.2891 3.7630 1.1046 -0.6448 -0.0174 -0.2198 -0.1714 0.0007 0.0000 0.0014 -0.0370 0.258 - 100 -1.5912 3.6435 1.1542 -0.6354 -0.0150 -0.2237 -0.1745 0.0005 0.0000 0.0008 -0.0371 0.254 - 101 -1.9146 3.5155 1.1831 -0.6229 -0.0125 -0.2273 -0.1773 0.0003 0.0000 0.0003 -0.0373 0.252 - 102 -2.2558 3.3805 1.1921 -0.6075 -0.0106 -0.2306 -0.1798 0.0001 0.0000 -0.0001 -0.0374 0.249 - 103 -2.6109 3.2400 1.1821 -0.5884 -0.0095 -0.2330 -0.1817 -0.0000 0.0000 -0.0004 -0.0376 0.248 - 104 -2.9762 3.0955 1.1548 -0.5667 -0.0091 -0.2349 -0.1832 -0.0001 0.0000 -0.0006 -0.0377 0.247 - 105 -3.3476 2.9485 1.1122 -0.5421 -0.0093 -0.2359 -0.1840 -0.0002 0.0000 -0.0007 -0.0378 0.246 - 106 -3.7210 2.8008 1.0564 -0.5154 -0.0098 -0.2361 -0.1841 -0.0002 0.0000 -0.0009 -0.0377 0.245 - 107 -4.0924 2.6538 0.9900 -0.4872 -0.0104 -0.2356 -0.1837 -0.0002 0.0000 -0.0010 -0.0375 0.245 - 108 -4.4577 2.5093 0.9155 -0.4578 -0.0112 -0.2341 -0.1826 -0.0002 0.0000 -0.0012 -0.0371 0.244 - 109 -4.8128 2.3687 0.8353 -0.4279 -0.0121 -0.2318 -0.1808 -0.0002 0.0000 -0.0014 -0.0365 0.242 - 110 -5.1540 2.2338 0.7518 -0.3976 -0.0131 -0.2284 -0.1781 -0.0001 0.0000 -0.0017 -0.0357 0.240 - 111 -5.4774 2.1058 0.6671 -0.3669 -0.0143 -0.2235 -0.1743 -0.0001 0.0000 -0.0022 -0.0345 0.237 - 112 -5.7795 1.9862 0.5830 -0.3361 -0.0157 -0.2171 -0.1693 -0.0002 0.0000 -0.0029 -0.0329 0.233 - 113 -6.0570 1.8764 0.5012 -0.3046 -0.0172 -0.2083 -0.1625 -0.0002 0.0000 -0.0037 -0.0307 0.227 - 114 -6.3069 1.7776 0.4225 -0.2726 -0.0189 -0.1967 -0.1534 -0.0002 0.0000 -0.0048 -0.0280 0.219 - 115 -6.5264 1.6907 0.3478 -0.2392 -0.0205 -0.1815 -0.1416 -0.0003 0.0000 -0.0060 -0.0245 0.208 - 116 -6.7314 1.6096 0.3326 -0.2024 -0.0222 -0.1614 -0.1259 -0.0003 0.0000 -0.0071 -0.0202 0.193 - 117 -6.9144 1.5372 0.2507 -0.1609 -0.0238 -0.1343 -0.1047 -0.0004 0.0000 -0.0079 -0.0152 0.175 - 118 -7.0535 1.4822 0.1746 -0.1168 -0.0250 -0.1012 -0.0789 -0.0005 0.0000 -0.0075 -0.0101 0.155 - 119 -7.1471 1.4451 0.1029 -0.0709 -0.0259 -0.0630 -0.0491 -0.0005 0.0000 -0.0055 -0.0056 0.138 - 120 -7.1941 1.4265 0.0340 -0.0238 -0.0264 -0.0214 -0.0167 -0.0005 0.0000 -0.0020 -0.0017 0.127 + 91 -0.0047 4.2713 0.0803 -0.5783 -0.0206 -0.1713 -0.1336 0.0541 0.0000 0.0080 -0.0350 0.310 + 92 -0.0418 4.2566 0.2392 -0.6544 -0.0210 -0.1970 -0.1536 0.0065 0.0000 0.0076 -0.0385 0.299 + 93 -0.1156 4.2274 0.3930 -0.6603 -0.0215 -0.2002 -0.1562 0.0034 0.0000 0.0071 -0.0386 0.295 + 94 -0.2254 4.1839 0.5386 -0.6619 -0.0217 -0.2028 -0.1582 0.0026 0.0000 0.0063 -0.0383 0.290 + 95 -0.3698 4.1268 0.6730 -0.6620 -0.0217 -0.2057 -0.1604 0.0021 0.0000 0.0052 -0.0379 0.283 + 96 -0.5474 4.0565 0.7936 -0.6614 -0.0214 -0.2091 -0.1631 0.0018 0.0000 0.0042 -0.0376 0.276 + 97 -0.7617 3.9717 0.9441 -0.6591 -0.0207 -0.2129 -0.1660 0.0014 0.0000 0.0031 -0.0373 0.269 + 98 -1.0116 3.8728 1.0344 -0.6554 -0.0193 -0.2171 -0.1693 0.0010 0.0000 0.0022 -0.0372 0.263 + 99 -1.2891 3.7630 1.1046 -0.6486 -0.0173 -0.2211 -0.1724 0.0007 0.0000 0.0014 -0.0372 0.258 + 100 -1.5912 3.6435 1.1542 -0.6392 -0.0149 -0.2251 -0.1755 0.0004 0.0000 0.0008 -0.0373 0.254 + 101 -1.9146 3.5155 1.1831 -0.6267 -0.0124 -0.2287 -0.1784 0.0002 0.0000 0.0003 -0.0375 0.252 + 102 -2.2558 3.3805 1.1921 -0.6110 -0.0105 -0.2319 -0.1809 0.0001 0.0000 -0.0001 -0.0377 0.249 + 103 -2.6109 3.2400 1.1821 -0.5918 -0.0094 -0.2344 -0.1828 -0.0000 0.0000 -0.0004 -0.0378 0.248 + 104 -2.9762 3.0955 1.1548 -0.5696 -0.0090 -0.2361 -0.1841 -0.0001 0.0000 -0.0006 -0.0379 0.247 + 105 -3.3476 2.9485 1.1122 -0.5449 -0.0092 -0.2371 -0.1849 -0.0002 0.0000 -0.0008 -0.0380 0.246 + 106 -3.7210 2.8008 1.0564 -0.5180 -0.0097 -0.2373 -0.1851 -0.0002 0.0000 -0.0009 -0.0379 0.245 + 107 -4.0924 2.6538 0.9900 -0.4894 -0.0103 -0.2366 -0.1845 -0.0002 0.0000 -0.0010 -0.0377 0.244 + 108 -4.4577 2.5093 0.9155 -0.4598 -0.0111 -0.2351 -0.1833 -0.0002 0.0000 -0.0012 -0.0373 0.244 + 109 -4.8128 2.3687 0.8353 -0.4295 -0.0120 -0.2326 -0.1814 -0.0002 0.0000 -0.0014 -0.0367 0.242 + 110 -5.1540 2.2338 0.7518 -0.3989 -0.0131 -0.2291 -0.1787 -0.0002 0.0000 -0.0017 -0.0358 0.240 + 111 -5.4774 2.1058 0.6671 -0.3680 -0.0143 -0.2242 -0.1749 -0.0001 0.0000 -0.0022 -0.0346 0.237 + 112 -5.7795 1.9862 0.5830 -0.3371 -0.0156 -0.2178 -0.1698 -0.0002 0.0000 -0.0029 -0.0330 0.233 + 113 -6.0570 1.8764 0.5012 -0.3054 -0.0172 -0.2089 -0.1629 -0.0002 0.0000 -0.0037 -0.0308 0.227 + 114 -6.3069 1.7776 0.4225 -0.2731 -0.0189 -0.1972 -0.1538 -0.0002 0.0000 -0.0048 -0.0280 0.219 + 115 -6.5264 1.6907 0.3478 -0.2396 -0.0205 -0.1819 -0.1418 -0.0003 0.0000 -0.0060 -0.0245 0.208 + 116 -6.7314 1.6096 0.3326 -0.2028 -0.0222 -0.1617 -0.1261 -0.0004 0.0000 -0.0071 -0.0203 0.194 + 117 -6.9144 1.5372 0.2507 -0.1612 -0.0238 -0.1346 -0.1050 -0.0004 0.0000 -0.0079 -0.0152 0.175 + 118 -7.0535 1.4822 0.1746 -0.1170 -0.0250 -0.1013 -0.0790 -0.0005 0.0000 -0.0075 -0.0102 0.155 + 119 -7.1471 1.4451 0.1029 -0.0710 -0.0259 -0.0631 -0.0492 -0.0005 0.0000 -0.0055 -0.0056 0.138 + 120 -7.1941 1.4265 0.0340 -0.0238 -0.0264 -0.0214 -0.0167 -0.0005 0.0000 -0.0020 -0.0018 0.127 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = -0.00000 CYsurf = -0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = 0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.807 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.789 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.776 - 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.757 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.732 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.700 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.658 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.613 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.557 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.486 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.429 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.401 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.374 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.355 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.336 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.324 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.309 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.297 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.285 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.277 - 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.274 - 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.265 + 121 0.0000 10.0347 0.6931 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.760 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.758 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.747 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.738 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.715 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.683 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.657 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.613 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.560 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.488 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.434 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.400 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.367 + 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.343 + 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.324 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.314 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.301 + 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.289 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.281 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.276 + 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.273 + 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.266 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.258 - 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.247 - 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.235 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.220 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.204 - 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.181 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.165 + 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.249 + 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.234 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.219 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.200 + 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.177 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.156 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.148 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00972 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.02402 - CDsurf = 0.00022 Cnsurf = 0.00000 + CLsurf = -0.00979 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = -0.02395 + CDsurf = 0.00022 Cnsurf = -0.00000 CDisurf = 0.00022 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00980 CDsurf = 0.00022 + CLsurf = -0.00987 CDsurf = 0.00022 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.2425 -0.0595 -0.1134 -0.0091 0.0001 0.0000 -0.0004 0.0003 0.209 - 152 -1.3090 31.2096 11.6724 -0.3265 -0.0550 -0.0407 -0.0105 0.0002 0.0000 -0.0008 0.0004 0.172 - 153 -0.9350 34.0626 12.7394 -0.3472 -0.0333 -0.0249 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.093 - 154 -0.5610 36.1619 13.5246 -0.3524 -0.0218 -0.0164 -0.0097 0.0003 0.0000 -0.0021 0.0002 0.037 - 155 -0.1870 37.5332 14.0374 -0.3537 -0.0173 -0.0109 -0.0094 0.0003 0.0000 -0.0023 0.0001 0.008 - 156 0.1870 37.5332 14.0374 -0.3537 -0.0173 -0.0109 -0.0094 0.0003 0.0000 -0.0023 0.0001 0.008 - 157 0.5610 36.1619 13.5246 -0.3524 -0.0218 -0.0164 -0.0097 0.0003 0.0000 -0.0021 0.0002 0.037 - 158 0.9350 34.0626 12.7394 -0.3472 -0.0333 -0.0249 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.093 - 159 1.3090 31.2096 11.6724 -0.3265 -0.0550 -0.0407 -0.0105 0.0002 0.0000 -0.0008 0.0004 0.172 - 160 1.6830 26.5957 9.9468 -0.2425 -0.0595 -0.1134 -0.0091 0.0001 0.0000 -0.0004 0.0003 0.209 + 151 -1.6830 26.5957 9.9468 -0.2442 -0.0595 -0.1142 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.212 + 152 -1.3090 31.2096 11.6724 -0.3288 -0.0550 -0.0410 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.174 + 153 -0.9350 34.0626 12.7394 -0.3497 -0.0331 -0.0250 -0.0103 0.0002 0.0000 -0.0016 0.0003 0.096 + 154 -0.5610 36.1619 13.5246 -0.3549 -0.0216 -0.0165 -0.0098 0.0003 0.0000 -0.0021 0.0002 0.040 + 155 -0.1870 37.5332 14.0374 -0.3562 -0.0170 -0.0110 -0.0095 0.0003 0.0000 -0.0023 0.0001 0.012 + 156 0.1870 37.5332 14.0374 -0.3562 -0.0170 -0.0110 -0.0095 0.0003 0.0000 -0.0023 0.0001 0.012 + 157 0.5610 36.1619 13.5246 -0.3549 -0.0216 -0.0165 -0.0098 0.0003 0.0000 -0.0021 0.0002 0.040 + 158 0.9350 34.0626 12.7394 -0.3497 -0.0331 -0.0250 -0.0103 0.0002 0.0000 -0.0016 0.0003 0.096 + 159 1.3090 31.2096 11.6724 -0.3288 -0.0550 -0.0410 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.174 + 160 1.6830 26.5957 9.9468 -0.2442 -0.0595 -0.1142 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.212 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.914 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.860 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.845 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.834 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.827 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.799 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.776 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.725 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.600 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.388 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.872 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.854 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.857 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.857 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.852 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.833 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.807 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.746 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.625 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.447 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_02_02.txt b/regression/scripts/AVL/avl_files/strip_forces_case_02_02.txt index 7751611b95..3170473a0a 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_02_02.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_02_02.txt @@ -7,252 +7,252 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09064 Clsurf = -0.01441 - CYsurf = -0.00615 Cmsurf = -0.07224 - CDsurf = 0.00122 Cnsurf = 0.00068 - CDisurf = 0.00122 CDvsurf = 0.00000 + CLsurf = 0.09123 Clsurf = -0.01447 + CYsurf = -0.00615 Cmsurf = -0.07256 + CDsurf = 0.00120 Cnsurf = 0.00068 + CDisurf = 0.00120 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.17732 CDsurf = 0.00238 + CLsurf = 0.17849 CDsurf = 0.00235 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 1.5898 0.0483 0.2644 0.2051 0.0735 0.0000 -0.0103 -0.0502 0.300 - 2 0.1025 7.6885 1.0492 1.5414 0.0476 0.2585 0.2005 0.0165 0.0000 -0.0104 -0.0493 0.302 - 3 0.2837 7.5620 1.7073 1.5338 0.0460 0.2615 0.2028 0.0127 0.0000 -0.0096 -0.0492 0.297 - 4 0.5530 7.3741 2.3052 1.5216 0.0434 0.2660 0.2063 0.0111 0.0000 -0.0085 -0.0490 0.291 - 5 0.9075 7.1267 2.8223 1.4977 0.0402 0.2710 0.2102 0.0097 0.0000 -0.0075 -0.0489 0.286 - 6 1.3432 6.8226 3.2414 1.4574 0.0380 0.2754 0.2136 0.0079 0.0000 -0.0067 -0.0490 0.282 - 7 1.8554 6.4651 3.5491 1.3967 0.0399 0.2785 0.2160 0.0067 0.0000 -0.0064 -0.0492 0.280 - 8 2.4386 6.0582 3.7368 1.3124 0.0401 0.2793 0.2166 0.0044 0.0000 -0.0067 -0.0496 0.281 - 9 3.0862 5.6062 3.8005 1.2043 0.0313 0.2770 0.2148 0.0027 0.0000 -0.0078 -0.0501 0.286 - 10 3.7613 5.1351 3.4440 1.0841 0.0210 0.2722 0.2111 0.0013 0.0000 -0.0097 -0.0509 0.296 - 11 4.4532 4.6522 3.3149 0.9564 0.0113 0.2651 0.2056 -0.0006 0.0000 -0.0127 -0.0523 0.312 - 12 5.1831 4.1429 3.0930 0.8215 -0.0015 0.2557 0.1983 -0.0023 0.0000 -0.0169 -0.0542 0.335 - 13 6.0123 3.7903 3.4706 0.7001 -0.0085 0.2249 0.1847 -0.0027 0.0000 -0.0198 -0.0587 0.357 - 14 6.9353 3.6075 3.3775 0.6138 -0.0057 0.2072 0.1701 -0.0019 0.0000 -0.0204 -0.0559 0.370 - 15 7.8737 3.4215 3.2389 0.5452 -0.0037 0.1941 0.1593 -0.0015 0.0000 -0.0205 -0.0536 0.379 - 16 8.8172 3.2345 3.0619 0.4886 -0.0024 0.1840 0.1511 -0.0012 0.0000 -0.0205 -0.0518 0.386 - 17 9.7556 3.0486 2.8543 0.4407 -0.0015 0.1760 0.1445 -0.0010 0.0000 -0.0204 -0.0503 0.391 - 18 10.6786 2.8657 2.6240 0.3992 -0.0009 0.1697 0.1393 -0.0009 0.0000 -0.0203 -0.0490 0.396 - 19 11.5760 2.6879 2.3787 0.3628 -0.0004 0.1644 0.1350 -0.0008 0.0000 -0.0203 -0.0480 0.400 - 20 12.4328 2.5181 2.1010 0.3306 0.0001 0.1599 0.1313 -0.0007 0.0000 -0.0202 -0.0471 0.404 - 21 13.2400 2.3582 1.8520 0.3014 0.0007 0.1557 0.1278 -0.0006 0.0000 -0.0200 -0.0462 0.407 - 22 13.9941 2.2087 1.6074 0.2745 0.0016 0.1514 0.1243 -0.0005 0.0000 -0.0198 -0.0452 0.410 - 23 14.6868 2.0715 1.3716 0.2489 0.0027 0.1463 0.1201 -0.0005 0.0000 -0.0195 -0.0440 0.412 - 24 15.3105 1.9479 1.1479 0.2234 0.0043 0.1397 0.1147 -0.0004 0.0000 -0.0190 -0.0424 0.416 - 25 15.8583 1.8393 0.9381 0.1966 0.0063 0.1302 0.1069 -0.0003 0.0000 -0.0182 -0.0399 0.420 - 26 16.3244 1.7470 0.7427 0.1669 0.0086 0.1163 0.0955 -0.0002 0.0000 -0.0171 -0.0364 0.429 - 27 16.6722 1.4928 0.4131 0.1348 0.0112 0.3015 0.0903 -0.0004 0.0000 -0.0144 -0.0173 0.410 - 28 16.9098 1.1466 0.2292 0.1019 0.0156 0.2966 0.0889 -0.0009 0.0000 -0.0102 -0.0152 0.365 - 29 17.0696 0.9138 0.1104 0.0643 0.0199 0.2347 0.0703 -0.0012 0.0000 -0.0044 -0.0103 0.312 - 30 17.1499 0.7967 0.0322 0.0220 0.0222 0.0922 0.0276 -0.0010 0.0000 -0.0007 -0.0035 0.274 + 1 0.0114 7.7520 0.3539 1.6058 0.0483 0.2671 0.2071 0.0734 0.0000 -0.0117 -0.0517 0.306 + 2 0.1025 7.6885 1.0491 1.5567 0.0476 0.2611 0.2025 0.0165 0.0000 -0.0116 -0.0507 0.307 + 3 0.2837 7.5620 1.7073 1.5493 0.0463 0.2641 0.2049 0.0127 0.0000 -0.0109 -0.0506 0.303 + 4 0.5530 7.3741 2.3052 1.5371 0.0440 0.2687 0.2084 0.0109 0.0000 -0.0098 -0.0505 0.297 + 5 0.9075 7.1267 2.8223 1.5134 0.0408 0.2738 0.2123 0.0096 0.0000 -0.0088 -0.0504 0.291 + 6 1.3432 6.8226 3.2414 1.4728 0.0386 0.2783 0.2159 0.0081 0.0000 -0.0080 -0.0505 0.287 + 7 1.8554 6.4651 3.5491 1.4111 0.0406 0.2814 0.2183 0.0059 0.0000 -0.0076 -0.0507 0.285 + 8 2.4386 6.0582 3.7368 1.3261 0.0407 0.2822 0.2189 0.0046 0.0000 -0.0077 -0.0509 0.285 + 9 3.0862 5.6062 3.8005 1.2180 0.0321 0.2801 0.2173 0.0028 0.0000 -0.0086 -0.0513 0.290 + 10 3.7613 5.1351 3.4440 1.0916 0.0216 0.2741 0.2126 0.0013 0.0000 -0.0103 -0.0517 0.299 + 11 4.4532 4.6522 3.3149 0.9637 0.0112 0.2671 0.2072 -0.0006 0.0000 -0.0126 -0.0524 0.311 + 12 5.1831 4.1429 3.0930 0.8248 -0.0021 0.2567 0.1991 -0.0023 0.0000 -0.0159 -0.0535 0.330 + 13 6.0123 3.7903 3.4706 0.7026 -0.0090 0.2257 0.1854 -0.0027 0.0000 -0.0184 -0.0575 0.349 + 14 6.9353 3.6075 3.3775 0.6158 -0.0060 0.2079 0.1707 -0.0019 0.0000 -0.0189 -0.0547 0.361 + 15 7.8737 3.4215 3.2389 0.5469 -0.0039 0.1947 0.1599 -0.0015 0.0000 -0.0189 -0.0523 0.368 + 16 8.8172 3.2345 3.0619 0.4901 -0.0025 0.1845 0.1515 -0.0012 0.0000 -0.0189 -0.0505 0.375 + 17 9.7556 3.0486 2.8543 0.4419 -0.0016 0.1765 0.1450 -0.0010 0.0000 -0.0188 -0.0489 0.380 + 18 10.6786 2.8657 2.6239 0.4003 -0.0010 0.1701 0.1397 -0.0009 0.0000 -0.0187 -0.0477 0.384 + 19 11.5760 2.6879 2.3787 0.3637 -0.0005 0.1648 0.1353 -0.0008 0.0000 -0.0187 -0.0467 0.388 + 20 12.4328 2.5181 2.1010 0.3313 0.0001 0.1602 0.1316 -0.0007 0.0000 -0.0186 -0.0457 0.391 + 21 13.2400 2.3582 1.8520 0.3021 0.0007 0.1560 0.1281 -0.0006 0.0000 -0.0184 -0.0448 0.394 + 22 13.9941 2.2087 1.6074 0.2750 0.0016 0.1516 0.1245 -0.0005 0.0000 -0.0182 -0.0439 0.396 + 23 14.6868 2.0715 1.3716 0.2492 0.0027 0.1465 0.1203 -0.0005 0.0000 -0.0179 -0.0426 0.399 + 24 15.3105 1.9479 1.1479 0.2236 0.0043 0.1398 0.1148 -0.0004 0.0000 -0.0174 -0.0409 0.401 + 25 15.8583 1.8393 0.9381 0.1965 0.0062 0.1301 0.1069 -0.0003 0.0000 -0.0165 -0.0384 0.405 + 26 16.3244 1.7470 0.7427 0.1664 0.0083 0.1160 0.0953 -0.0002 0.0000 -0.0155 -0.0350 0.413 + 27 16.6722 1.4928 0.4131 0.1344 0.0108 0.3006 0.0900 -0.0005 0.0000 -0.0132 -0.0167 0.396 + 28 16.9098 1.1466 0.2292 0.1018 0.0155 0.2962 0.0887 -0.0009 0.0000 -0.0092 -0.0147 0.354 + 29 17.0696 0.9138 0.1104 0.0643 0.0200 0.2348 0.0703 -0.0013 0.0000 -0.0038 -0.0100 0.304 + 30 17.1499 0.7967 0.0322 0.0221 0.0229 0.0925 0.0277 -0.0010 0.0000 -0.0005 -0.0035 0.268 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09063 Clsurf = 0.01441 - CYsurf = 0.00615 Cmsurf = -0.07224 - CDsurf = 0.00122 Cnsurf = -0.00068 - CDisurf = 0.00122 CDvsurf = 0.00000 + CLsurf = 0.09123 Clsurf = 0.01447 + CYsurf = 0.00615 Cmsurf = -0.07256 + CDsurf = 0.00120 Cnsurf = -0.00068 + CDisurf = 0.00120 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.17732 CDsurf = 0.00238 + CLsurf = 0.17849 CDsurf = 0.00235 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 1.5898 0.0483 0.2644 0.2051 0.0735 0.0000 -0.0103 0.0502 0.300 - 32 -0.1025 7.6885 1.0492 1.5414 0.0476 0.2585 0.2005 0.0165 0.0000 -0.0104 0.0493 0.302 - 33 -0.2837 7.5620 1.7073 1.5338 0.0460 0.2615 0.2028 0.0127 0.0000 -0.0096 0.0492 0.297 - 34 -0.5530 7.3741 2.3052 1.5216 0.0434 0.2660 0.2063 0.0111 0.0000 -0.0085 0.0490 0.291 - 35 -0.9075 7.1267 2.8223 1.4977 0.0402 0.2710 0.2102 0.0097 0.0000 -0.0075 0.0489 0.286 - 36 -1.3432 6.8226 3.2414 1.4574 0.0380 0.2754 0.2136 0.0079 0.0000 -0.0067 0.0490 0.282 - 37 -1.8554 6.4651 3.5491 1.3967 0.0399 0.2785 0.2160 0.0067 0.0000 -0.0064 0.0492 0.280 - 38 -2.4386 6.0582 3.7368 1.3124 0.0401 0.2793 0.2166 0.0044 0.0000 -0.0067 0.0496 0.281 - 39 -3.0862 5.6062 3.8005 1.2043 0.0313 0.2770 0.2148 0.0027 0.0000 -0.0078 0.0501 0.286 - 40 -3.7613 5.1351 3.4440 1.0841 0.0210 0.2722 0.2111 0.0013 0.0000 -0.0097 0.0509 0.296 - 41 -4.4532 4.6522 3.3149 0.9564 0.0113 0.2651 0.2056 -0.0006 0.0000 -0.0127 0.0523 0.312 - 42 -5.1831 4.1429 3.0930 0.8215 -0.0015 0.2557 0.1983 -0.0023 0.0000 -0.0169 0.0541 0.335 - 43 -6.0123 3.7903 3.4706 0.7001 -0.0085 0.2249 0.1847 -0.0027 0.0000 -0.0198 0.0587 0.357 - 44 -6.9353 3.6075 3.3775 0.6138 -0.0057 0.2072 0.1701 -0.0019 0.0000 -0.0204 0.0559 0.370 - 45 -7.8737 3.4215 3.2389 0.5452 -0.0037 0.1941 0.1593 -0.0015 0.0000 -0.0205 0.0536 0.379 - 46 -8.8172 3.2345 3.0619 0.4886 -0.0024 0.1840 0.1511 -0.0012 0.0000 -0.0205 0.0518 0.386 - 47 -9.7556 3.0486 2.8543 0.4407 -0.0015 0.1760 0.1445 -0.0010 0.0000 -0.0204 0.0503 0.391 - 48 -10.6786 2.8657 2.6240 0.3992 -0.0009 0.1697 0.1393 -0.0009 0.0000 -0.0203 0.0490 0.396 - 49 -11.5760 2.6879 2.3787 0.3628 -0.0004 0.1644 0.1350 -0.0008 0.0000 -0.0203 0.0480 0.400 - 50 -12.4328 2.5181 2.1010 0.3306 0.0001 0.1599 0.1313 -0.0007 0.0000 -0.0202 0.0471 0.404 - 51 -13.2400 2.3582 1.8520 0.3014 0.0007 0.1557 0.1278 -0.0006 0.0000 -0.0200 0.0462 0.407 - 52 -13.9941 2.2087 1.6074 0.2745 0.0016 0.1514 0.1243 -0.0005 0.0000 -0.0198 0.0452 0.410 - 53 -14.6868 2.0715 1.3716 0.2489 0.0027 0.1463 0.1201 -0.0005 0.0000 -0.0195 0.0440 0.412 - 54 -15.3105 1.9479 1.1479 0.2234 0.0043 0.1397 0.1147 -0.0004 0.0000 -0.0190 0.0424 0.416 - 55 -15.8583 1.8393 0.9381 0.1966 0.0063 0.1302 0.1069 -0.0003 0.0000 -0.0182 0.0399 0.420 - 56 -16.3244 1.7470 0.7427 0.1669 0.0086 0.1163 0.0955 -0.0002 0.0000 -0.0171 0.0364 0.429 - 57 -16.6722 1.4928 0.4131 0.1348 0.0112 0.3015 0.0903 -0.0004 0.0000 -0.0144 0.0173 0.410 - 58 -16.9098 1.1466 0.2292 0.1019 0.0156 0.2966 0.0889 -0.0009 0.0000 -0.0102 0.0152 0.365 - 59 -17.0696 0.9138 0.1104 0.0643 0.0199 0.2347 0.0703 -0.0012 0.0000 -0.0044 0.0103 0.312 - 60 -17.1499 0.7967 0.0322 0.0220 0.0222 0.0922 0.0276 -0.0010 0.0000 -0.0007 0.0035 0.274 + 31 -0.0114 7.7520 0.3539 1.6058 0.0482 0.2671 0.2071 0.0734 0.0000 -0.0117 0.0517 0.306 + 32 -0.1025 7.6885 1.0491 1.5567 0.0476 0.2611 0.2025 0.0165 0.0000 -0.0116 0.0507 0.307 + 33 -0.2837 7.5620 1.7073 1.5493 0.0463 0.2641 0.2049 0.0127 0.0000 -0.0109 0.0506 0.303 + 34 -0.5530 7.3741 2.3052 1.5371 0.0440 0.2687 0.2084 0.0109 0.0000 -0.0098 0.0505 0.297 + 35 -0.9075 7.1267 2.8223 1.5134 0.0408 0.2738 0.2123 0.0096 0.0000 -0.0088 0.0504 0.291 + 36 -1.3432 6.8226 3.2414 1.4728 0.0386 0.2783 0.2159 0.0081 0.0000 -0.0080 0.0505 0.287 + 37 -1.8554 6.4651 3.5491 1.4111 0.0406 0.2814 0.2183 0.0059 0.0000 -0.0076 0.0507 0.285 + 38 -2.4386 6.0582 3.7368 1.3261 0.0407 0.2822 0.2189 0.0046 0.0000 -0.0077 0.0509 0.285 + 39 -3.0862 5.6062 3.8005 1.2180 0.0321 0.2801 0.2173 0.0028 0.0000 -0.0086 0.0513 0.290 + 40 -3.7613 5.1351 3.4440 1.0916 0.0216 0.2741 0.2126 0.0013 0.0000 -0.0103 0.0517 0.299 + 41 -4.4532 4.6522 3.3149 0.9637 0.0112 0.2671 0.2072 -0.0006 0.0000 -0.0126 0.0524 0.311 + 42 -5.1831 4.1429 3.0930 0.8248 -0.0021 0.2567 0.1991 -0.0023 0.0000 -0.0159 0.0535 0.330 + 43 -6.0123 3.7903 3.4706 0.7026 -0.0090 0.2257 0.1854 -0.0027 0.0000 -0.0184 0.0575 0.349 + 44 -6.9353 3.6075 3.3775 0.6158 -0.0060 0.2079 0.1707 -0.0019 0.0000 -0.0189 0.0547 0.361 + 45 -7.8737 3.4215 3.2389 0.5469 -0.0039 0.1947 0.1599 -0.0015 0.0000 -0.0189 0.0523 0.368 + 46 -8.8172 3.2345 3.0619 0.4901 -0.0025 0.1845 0.1515 -0.0012 0.0000 -0.0189 0.0505 0.375 + 47 -9.7556 3.0486 2.8543 0.4419 -0.0016 0.1765 0.1450 -0.0010 0.0000 -0.0188 0.0489 0.380 + 48 -10.6786 2.8657 2.6239 0.4003 -0.0010 0.1701 0.1397 -0.0009 0.0000 -0.0187 0.0477 0.384 + 49 -11.5760 2.6879 2.3787 0.3637 -0.0005 0.1648 0.1353 -0.0008 0.0000 -0.0187 0.0467 0.388 + 50 -12.4328 2.5181 2.1010 0.3313 0.0001 0.1602 0.1316 -0.0007 0.0000 -0.0186 0.0457 0.391 + 51 -13.2400 2.3582 1.8520 0.3021 0.0007 0.1560 0.1281 -0.0006 0.0000 -0.0184 0.0448 0.394 + 52 -13.9941 2.2087 1.6074 0.2750 0.0016 0.1516 0.1245 -0.0005 0.0000 -0.0182 0.0439 0.396 + 53 -14.6868 2.0715 1.3716 0.2492 0.0027 0.1465 0.1203 -0.0005 0.0000 -0.0179 0.0426 0.399 + 54 -15.3105 1.9479 1.1479 0.2236 0.0043 0.1398 0.1148 -0.0004 0.0000 -0.0174 0.0409 0.401 + 55 -15.8583 1.8393 0.9381 0.1965 0.0062 0.1301 0.1069 -0.0003 0.0000 -0.0165 0.0384 0.405 + 56 -16.3244 1.7470 0.7427 0.1664 0.0083 0.1160 0.0953 -0.0002 0.0000 -0.0155 0.0350 0.413 + 57 -16.6722 1.4928 0.4131 0.1344 0.0108 0.3006 0.0900 -0.0005 0.0000 -0.0132 0.0167 0.396 + 58 -16.9098 1.1466 0.2292 0.1018 0.0155 0.2962 0.0887 -0.0009 0.0000 -0.0092 0.0147 0.354 + 59 -17.0696 0.9138 0.1104 0.0643 0.0200 0.2348 0.0703 -0.0013 0.0000 -0.0038 0.0100 0.304 + 60 -17.1499 0.7967 0.0322 0.0221 0.0229 0.0925 0.0277 -0.0010 0.0000 -0.0005 0.0035 0.268 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01247 Clsurf = 0.00113 - CYsurf = 0.00200 Cmsurf = 0.05958 - CDsurf = -0.00018 Cnsurf = -0.00120 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01261 Clsurf = 0.00114 + CYsurf = 0.00203 Cmsurf = 0.06022 + CDsurf = -0.00018 Cnsurf = -0.00121 CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.07605 CDsurf = -0.00106 + CLsurf = -0.07687 CDsurf = -0.00109 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.3069 0.0109 -0.0927 -0.0718 0.0122 0.0000 0.0033 0.0180 0.296 - 62 0.0418 4.2566 0.2392 -0.3256 0.0107 -0.0987 -0.0765 0.0003 0.0000 0.0031 0.0188 0.291 - 63 0.1156 4.2274 0.3930 -0.3270 0.0104 -0.0998 -0.0774 -0.0005 0.0000 0.0029 0.0188 0.287 - 64 0.2254 4.1839 0.5386 -0.3274 0.0101 -0.1009 -0.0782 -0.0007 0.0000 0.0025 0.0186 0.282 - 65 0.3698 4.1268 0.6730 -0.3271 0.0098 -0.1022 -0.0793 -0.0009 0.0000 0.0020 0.0184 0.275 - 66 0.5474 4.0565 0.7936 -0.3262 0.0096 -0.1037 -0.0804 -0.0010 0.0000 0.0014 0.0182 0.268 - 67 0.7617 3.9717 0.9441 -0.3246 0.0094 -0.1054 -0.0817 -0.0011 0.0000 0.0009 0.0180 0.261 - 68 1.0116 3.8728 1.0344 -0.3215 0.0095 -0.1071 -0.0830 -0.0012 0.0000 0.0004 0.0179 0.255 - 69 1.2891 3.7630 1.1046 -0.3170 0.0098 -0.1087 -0.0842 -0.0013 0.0000 0.0000 0.0178 0.250 - 70 1.5912 3.6435 1.1542 -0.3104 0.0103 -0.1099 -0.0852 -0.0014 0.0000 -0.0003 0.0177 0.247 - 71 1.9146 3.5155 1.1831 -0.3017 0.0108 -0.1107 -0.0858 -0.0014 0.0000 -0.0005 0.0176 0.244 - 72 2.2558 3.3805 1.1921 -0.2907 0.0110 -0.1109 -0.0860 -0.0015 0.0000 -0.0007 0.0175 0.242 - 73 2.6109 3.2400 1.1821 -0.2774 0.0109 -0.1104 -0.0856 -0.0015 0.0000 -0.0008 0.0174 0.240 - 74 2.9762 3.0955 1.1548 -0.2621 0.0104 -0.1092 -0.0847 -0.0014 0.0000 -0.0009 0.0171 0.239 - 75 3.3476 2.9485 1.1122 -0.2451 0.0097 -0.1072 -0.0831 -0.0014 0.0000 -0.0009 0.0168 0.239 - 76 3.7210 2.8008 1.0564 -0.2269 0.0090 -0.1045 -0.0810 -0.0013 0.0000 -0.0009 0.0163 0.239 - 77 4.0924 2.6538 0.9900 -0.2081 0.0083 -0.1011 -0.0784 -0.0012 0.0000 -0.0009 0.0158 0.239 - 78 4.4577 2.5093 0.9155 -0.1891 0.0075 -0.0972 -0.0753 -0.0011 0.0000 -0.0009 0.0152 0.238 - 79 4.8128 2.3687 0.8353 -0.1704 0.0069 -0.0928 -0.0720 -0.0010 0.0000 -0.0009 0.0144 0.238 - 80 5.1540 2.2338 0.7518 -0.1525 0.0063 -0.0881 -0.0683 -0.0009 0.0000 -0.0009 0.0136 0.237 - 81 5.4774 2.1058 0.6671 -0.1355 0.0057 -0.0830 -0.0643 -0.0008 0.0000 -0.0010 0.0128 0.235 - 82 5.7795 1.9862 0.5830 -0.1195 0.0050 -0.0776 -0.0602 -0.0008 0.0000 -0.0011 0.0118 0.232 - 83 6.0570 1.8764 0.5012 -0.1045 0.0044 -0.0719 -0.0557 -0.0007 0.0000 -0.0013 0.0107 0.227 - 84 6.3069 1.7776 0.4225 -0.0905 0.0038 -0.0656 -0.0509 -0.0006 0.0000 -0.0015 0.0095 0.220 - 85 6.5264 1.6907 0.3478 -0.0771 0.0033 -0.0588 -0.0456 -0.0005 0.0000 -0.0018 0.0081 0.211 - 86 6.7314 1.6096 0.3326 -0.0635 0.0027 -0.0509 -0.0394 -0.0004 0.0000 -0.0020 0.0066 0.198 - 87 6.9144 1.5372 0.2507 -0.0493 0.0022 -0.0413 -0.0320 -0.0004 0.0000 -0.0022 0.0049 0.181 - 88 7.0535 1.4822 0.1746 -0.0351 0.0018 -0.0306 -0.0237 -0.0003 0.0000 -0.0021 0.0033 0.163 - 89 7.1471 1.4451 0.1029 -0.0211 0.0015 -0.0188 -0.0146 -0.0002 0.0000 -0.0015 0.0018 0.146 - 90 7.1941 1.4265 0.0340 -0.0070 0.0014 -0.0064 -0.0049 -0.0001 0.0000 -0.0006 0.0006 0.136 + 61 0.0047 4.2713 0.0803 -0.3103 0.0110 -0.0937 -0.0727 0.0125 0.0000 0.0034 0.0182 0.296 + 62 0.0418 4.2566 0.2392 -0.3295 0.0108 -0.0999 -0.0774 0.0003 0.0000 0.0032 0.0190 0.291 + 63 0.1156 4.2274 0.3930 -0.3310 0.0105 -0.1010 -0.0783 -0.0005 0.0000 0.0029 0.0190 0.287 + 64 0.2254 4.1839 0.5386 -0.3313 0.0102 -0.1021 -0.0792 -0.0008 0.0000 0.0025 0.0188 0.282 + 65 0.3698 4.1268 0.6730 -0.3311 0.0099 -0.1035 -0.0802 -0.0009 0.0000 0.0020 0.0186 0.275 + 66 0.5474 4.0565 0.7936 -0.3303 0.0097 -0.1050 -0.0814 -0.0010 0.0000 0.0014 0.0184 0.268 + 67 0.7617 3.9717 0.9441 -0.3285 0.0095 -0.1067 -0.0827 -0.0011 0.0000 0.0009 0.0182 0.261 + 68 1.0116 3.8728 1.0344 -0.3255 0.0096 -0.1084 -0.0841 -0.0013 0.0000 0.0004 0.0181 0.255 + 69 1.2891 3.7630 1.1046 -0.3208 0.0099 -0.1100 -0.0852 -0.0014 0.0000 0.0000 0.0180 0.250 + 70 1.5912 3.6435 1.1542 -0.3141 0.0104 -0.1112 -0.0862 -0.0014 0.0000 -0.0003 0.0179 0.246 + 71 1.9146 3.5155 1.1831 -0.3053 0.0109 -0.1120 -0.0868 -0.0015 0.0000 -0.0006 0.0178 0.244 + 72 2.2558 3.3805 1.1921 -0.2941 0.0112 -0.1122 -0.0870 -0.0015 0.0000 -0.0007 0.0177 0.241 + 73 2.6109 3.2400 1.1821 -0.2806 0.0110 -0.1117 -0.0866 -0.0015 0.0000 -0.0009 0.0175 0.240 + 74 2.9762 3.0955 1.1548 -0.2651 0.0105 -0.1104 -0.0856 -0.0015 0.0000 -0.0009 0.0173 0.239 + 75 3.3476 2.9485 1.1122 -0.2478 0.0099 -0.1084 -0.0840 -0.0014 0.0000 -0.0009 0.0169 0.239 + 76 3.7210 2.8008 1.0564 -0.2293 0.0091 -0.1056 -0.0819 -0.0013 0.0000 -0.0009 0.0165 0.239 + 77 4.0924 2.6538 0.9900 -0.2102 0.0083 -0.1022 -0.0792 -0.0013 0.0000 -0.0009 0.0159 0.238 + 78 4.4577 2.5093 0.9155 -0.1909 0.0076 -0.0981 -0.0761 -0.0012 0.0000 -0.0009 0.0153 0.238 + 79 4.8128 2.3687 0.8353 -0.1720 0.0069 -0.0936 -0.0726 -0.0011 0.0000 -0.0009 0.0146 0.238 + 80 5.1540 2.2338 0.7518 -0.1538 0.0063 -0.0888 -0.0688 -0.0010 0.0000 -0.0009 0.0138 0.237 + 81 5.4774 2.1058 0.6671 -0.1365 0.0057 -0.0836 -0.0648 -0.0008 0.0000 -0.0010 0.0129 0.235 + 82 5.7795 1.9862 0.5830 -0.1204 0.0051 -0.0782 -0.0606 -0.0008 0.0000 -0.0011 0.0119 0.232 + 83 6.0570 1.8764 0.5012 -0.1052 0.0045 -0.0723 -0.0561 -0.0007 0.0000 -0.0013 0.0108 0.227 + 84 6.3069 1.7776 0.4225 -0.0910 0.0039 -0.0661 -0.0512 -0.0006 0.0000 -0.0015 0.0095 0.220 + 85 6.5264 1.6907 0.3478 -0.0775 0.0033 -0.0592 -0.0459 -0.0005 0.0000 -0.0018 0.0082 0.211 + 86 6.7314 1.6096 0.3326 -0.0638 0.0027 -0.0512 -0.0397 -0.0004 0.0000 -0.0020 0.0066 0.198 + 87 6.9144 1.5372 0.2507 -0.0495 0.0022 -0.0416 -0.0322 -0.0004 0.0000 -0.0022 0.0049 0.181 + 88 7.0535 1.4822 0.1746 -0.0353 0.0018 -0.0307 -0.0238 -0.0003 0.0000 -0.0021 0.0033 0.163 + 89 7.1471 1.4451 0.1029 -0.0212 0.0015 -0.0189 -0.0147 -0.0002 0.0000 -0.0015 0.0018 0.146 + 90 7.1941 1.4265 0.0340 -0.0071 0.0014 -0.0064 -0.0049 -0.0001 0.0000 -0.0006 0.0006 0.136 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01247 Clsurf = -0.00113 - CYsurf = -0.00200 Cmsurf = 0.05958 - CDsurf = -0.00018 Cnsurf = 0.00120 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01261 Clsurf = -0.00114 + CYsurf = -0.00203 Cmsurf = 0.06022 + CDsurf = -0.00018 Cnsurf = 0.00121 CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.07604 CDsurf = -0.00106 + CLsurf = -0.07687 CDsurf = -0.00109 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.3069 0.0109 -0.0927 -0.0718 0.0122 0.0000 0.0033 -0.0180 0.296 - 92 -0.0418 4.2566 0.2392 -0.3256 0.0107 -0.0987 -0.0765 0.0003 0.0000 0.0031 -0.0188 0.291 - 93 -0.1156 4.2274 0.3930 -0.3270 0.0104 -0.0998 -0.0774 -0.0005 0.0000 0.0029 -0.0188 0.287 - 94 -0.2254 4.1839 0.5386 -0.3274 0.0101 -0.1009 -0.0782 -0.0007 0.0000 0.0025 -0.0186 0.282 - 95 -0.3698 4.1268 0.6730 -0.3271 0.0098 -0.1022 -0.0793 -0.0009 0.0000 0.0020 -0.0184 0.275 - 96 -0.5474 4.0565 0.7936 -0.3262 0.0096 -0.1037 -0.0804 -0.0010 0.0000 0.0014 -0.0182 0.268 - 97 -0.7617 3.9717 0.9441 -0.3246 0.0094 -0.1054 -0.0817 -0.0011 0.0000 0.0009 -0.0180 0.261 - 98 -1.0116 3.8728 1.0344 -0.3215 0.0095 -0.1071 -0.0830 -0.0012 0.0000 0.0004 -0.0179 0.255 - 99 -1.2891 3.7630 1.1046 -0.3170 0.0098 -0.1087 -0.0842 -0.0013 0.0000 0.0000 -0.0178 0.250 - 100 -1.5912 3.6435 1.1542 -0.3104 0.0103 -0.1099 -0.0852 -0.0014 0.0000 -0.0003 -0.0177 0.247 - 101 -1.9146 3.5155 1.1831 -0.3016 0.0108 -0.1107 -0.0858 -0.0014 0.0000 -0.0005 -0.0176 0.244 - 102 -2.2558 3.3805 1.1921 -0.2907 0.0110 -0.1109 -0.0860 -0.0015 0.0000 -0.0007 -0.0175 0.242 - 103 -2.6109 3.2400 1.1821 -0.2774 0.0109 -0.1104 -0.0856 -0.0015 0.0000 -0.0008 -0.0174 0.240 - 104 -2.9762 3.0955 1.1548 -0.2621 0.0104 -0.1092 -0.0847 -0.0014 0.0000 -0.0009 -0.0171 0.239 - 105 -3.3476 2.9485 1.1122 -0.2451 0.0097 -0.1072 -0.0831 -0.0014 0.0000 -0.0009 -0.0168 0.239 - 106 -3.7210 2.8008 1.0564 -0.2269 0.0090 -0.1045 -0.0810 -0.0013 0.0000 -0.0009 -0.0163 0.239 - 107 -4.0924 2.6538 0.9900 -0.2081 0.0083 -0.1011 -0.0784 -0.0012 0.0000 -0.0009 -0.0158 0.239 - 108 -4.4577 2.5093 0.9155 -0.1891 0.0075 -0.0972 -0.0753 -0.0011 0.0000 -0.0009 -0.0152 0.238 - 109 -4.8128 2.3687 0.8353 -0.1704 0.0069 -0.0928 -0.0719 -0.0010 0.0000 -0.0009 -0.0144 0.238 - 110 -5.1540 2.2338 0.7518 -0.1525 0.0063 -0.0880 -0.0683 -0.0009 0.0000 -0.0009 -0.0136 0.237 - 111 -5.4774 2.1058 0.6671 -0.1354 0.0057 -0.0830 -0.0643 -0.0008 0.0000 -0.0010 -0.0128 0.235 - 112 -5.7795 1.9862 0.5830 -0.1195 0.0050 -0.0776 -0.0602 -0.0008 0.0000 -0.0011 -0.0118 0.232 - 113 -6.0570 1.8764 0.5012 -0.1045 0.0044 -0.0718 -0.0557 -0.0007 0.0000 -0.0013 -0.0107 0.227 - 114 -6.3069 1.7776 0.4225 -0.0905 0.0038 -0.0656 -0.0509 -0.0006 0.0000 -0.0015 -0.0095 0.220 - 115 -6.5264 1.6907 0.3478 -0.0771 0.0033 -0.0588 -0.0456 -0.0005 0.0000 -0.0018 -0.0081 0.211 - 116 -6.7314 1.6096 0.3326 -0.0635 0.0027 -0.0509 -0.0394 -0.0004 0.0000 -0.0020 -0.0066 0.198 - 117 -6.9144 1.5372 0.2507 -0.0493 0.0022 -0.0413 -0.0320 -0.0004 0.0000 -0.0022 -0.0049 0.181 - 118 -7.0535 1.4822 0.1746 -0.0351 0.0018 -0.0306 -0.0237 -0.0003 0.0000 -0.0021 -0.0033 0.163 - 119 -7.1471 1.4451 0.1029 -0.0211 0.0015 -0.0188 -0.0146 -0.0002 0.0000 -0.0015 -0.0018 0.146 - 120 -7.1941 1.4265 0.0340 -0.0070 0.0014 -0.0064 -0.0049 -0.0001 0.0000 -0.0006 -0.0006 0.136 + 91 -0.0047 4.2713 0.0803 -0.3103 0.0110 -0.0937 -0.0727 0.0125 0.0000 0.0034 -0.0182 0.296 + 92 -0.0418 4.2566 0.2392 -0.3295 0.0108 -0.0999 -0.0774 0.0003 0.0000 0.0032 -0.0190 0.291 + 93 -0.1156 4.2274 0.3930 -0.3310 0.0105 -0.1010 -0.0783 -0.0005 0.0000 0.0029 -0.0190 0.287 + 94 -0.2254 4.1839 0.5386 -0.3313 0.0102 -0.1021 -0.0792 -0.0008 0.0000 0.0025 -0.0188 0.282 + 95 -0.3698 4.1268 0.6730 -0.3311 0.0099 -0.1035 -0.0802 -0.0009 0.0000 0.0020 -0.0186 0.275 + 96 -0.5474 4.0565 0.7936 -0.3303 0.0097 -0.1050 -0.0814 -0.0010 0.0000 0.0014 -0.0184 0.268 + 97 -0.7617 3.9717 0.9441 -0.3285 0.0095 -0.1067 -0.0827 -0.0011 0.0000 0.0009 -0.0182 0.261 + 98 -1.0116 3.8728 1.0344 -0.3255 0.0096 -0.1084 -0.0841 -0.0013 0.0000 0.0004 -0.0181 0.255 + 99 -1.2891 3.7630 1.1046 -0.3208 0.0099 -0.1100 -0.0852 -0.0014 0.0000 0.0000 -0.0180 0.250 + 100 -1.5912 3.6435 1.1542 -0.3141 0.0104 -0.1112 -0.0862 -0.0014 0.0000 -0.0003 -0.0179 0.246 + 101 -1.9146 3.5155 1.1831 -0.3053 0.0109 -0.1120 -0.0868 -0.0015 0.0000 -0.0006 -0.0178 0.244 + 102 -2.2558 3.3805 1.1921 -0.2941 0.0112 -0.1122 -0.0870 -0.0015 0.0000 -0.0007 -0.0177 0.241 + 103 -2.6109 3.2400 1.1821 -0.2806 0.0110 -0.1117 -0.0866 -0.0015 0.0000 -0.0009 -0.0175 0.240 + 104 -2.9762 3.0955 1.1548 -0.2651 0.0105 -0.1104 -0.0856 -0.0015 0.0000 -0.0009 -0.0173 0.239 + 105 -3.3476 2.9485 1.1122 -0.2478 0.0099 -0.1084 -0.0840 -0.0014 0.0000 -0.0009 -0.0169 0.239 + 106 -3.7210 2.8008 1.0564 -0.2293 0.0091 -0.1056 -0.0819 -0.0013 0.0000 -0.0009 -0.0165 0.239 + 107 -4.0924 2.6538 0.9900 -0.2102 0.0083 -0.1022 -0.0792 -0.0013 0.0000 -0.0009 -0.0159 0.238 + 108 -4.4577 2.5093 0.9155 -0.1909 0.0076 -0.0981 -0.0761 -0.0012 0.0000 -0.0009 -0.0153 0.238 + 109 -4.8128 2.3687 0.8353 -0.1720 0.0069 -0.0936 -0.0726 -0.0011 0.0000 -0.0009 -0.0146 0.238 + 110 -5.1540 2.2338 0.7518 -0.1538 0.0063 -0.0888 -0.0688 -0.0010 0.0000 -0.0009 -0.0138 0.237 + 111 -5.4774 2.1058 0.6671 -0.1365 0.0057 -0.0836 -0.0648 -0.0008 0.0000 -0.0010 -0.0129 0.235 + 112 -5.7795 1.9862 0.5830 -0.1204 0.0051 -0.0782 -0.0606 -0.0008 0.0000 -0.0011 -0.0119 0.232 + 113 -6.0570 1.8764 0.5012 -0.1052 0.0045 -0.0723 -0.0561 -0.0007 0.0000 -0.0013 -0.0108 0.227 + 114 -6.3069 1.7776 0.4225 -0.0910 0.0039 -0.0661 -0.0512 -0.0006 0.0000 -0.0015 -0.0095 0.220 + 115 -6.5264 1.6907 0.3478 -0.0775 0.0033 -0.0592 -0.0459 -0.0005 0.0000 -0.0018 -0.0082 0.211 + 116 -6.7314 1.6096 0.3326 -0.0638 0.0027 -0.0512 -0.0397 -0.0004 0.0000 -0.0020 -0.0066 0.198 + 117 -6.9144 1.5372 0.2507 -0.0495 0.0022 -0.0416 -0.0322 -0.0004 0.0000 -0.0022 -0.0049 0.181 + 118 -7.0535 1.4822 0.1746 -0.0353 0.0018 -0.0307 -0.0238 -0.0003 0.0000 -0.0021 -0.0033 0.163 + 119 -7.1471 1.4451 0.1029 -0.0212 0.0015 -0.0189 -0.0147 -0.0002 0.0000 -0.0015 -0.0018 0.146 + 120 -7.1941 1.4265 0.0340 -0.0071 0.0014 -0.0064 -0.0049 -0.0001 0.0000 -0.0006 -0.0006 0.136 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.00000 - CDsurf = -0.00000 Cnsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.925 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.575 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.528 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.719 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 136 0.0000 3.2923 1.3482 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 137 0.0000 3.0597 1.2352 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.437 - 139 0.0000 2.6103 0.9908 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.128 - 140 0.0000 2.3983 0.8670 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.015 - 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.032 - 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.102 - 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.116 - 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.145 - 145 0.0000 1.5493 0.3400 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.136 - 146 0.0000 1.4342 0.2622 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.124 - 147 0.0000 1.3407 0.1933 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.105 - 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.103 - 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.063 - 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.052 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 126 0.0000 8.0598 2.2181 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 127 0.0000 7.4000 2.2957 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 128 0.0000 6.6646 2.2808 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 129 0.0000 5.8609 2.1733 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 130 0.0000 4.9969 1.9773 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.735 + 131 0.0000 4.4389 1.6667 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.565 + 132 0.0000 4.2198 1.6478 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.323 + 133 0.0000 3.9932 1.6033 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.159 + 134 0.0000 3.7615 1.5362 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.077 + 135 0.0000 3.5271 1.4499 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.022 + 136 0.0000 3.2923 1.3482 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.041 + 137 0.0000 3.0597 1.2352 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.094 + 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.122 + 139 0.0000 2.6103 0.9908 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.151 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.171 + 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.172 + 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.183 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.186 + 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.188 + 145 0.0000 1.5493 0.3400 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.192 + 146 0.0000 1.4342 0.2622 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.156 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.146 + 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.122 + 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.095 + 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.087 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00507 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.00363 + CLsurf = -0.00514 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00355 CDsurf = 0.00002 Cnsurf = 0.00000 CDisurf = 0.00002 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00511 CDsurf = 0.00002 + CLsurf = -0.00518 CDsurf = 0.00002 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.1326 -0.0064 -0.0629 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.411 - 152 -1.3090 31.2096 11.6724 -0.1731 -0.0001 -0.0216 -0.0055 0.0000 0.0000 0.0007 0.0005 0.373 - 153 -0.9350 34.0626 12.7394 -0.1805 0.0136 -0.0130 -0.0053 0.0000 0.0000 0.0003 0.0006 0.311 - 154 -0.5610 36.1619 13.5246 -0.1805 0.0215 -0.0084 -0.0050 0.0001 0.0000 0.0001 0.0006 0.266 - 155 -0.1870 37.5332 14.0374 -0.1796 0.0250 -0.0056 -0.0048 0.0001 0.0000 -0.0000 0.0008 0.243 - 156 0.1870 37.5332 14.0374 -0.1796 0.0250 -0.0056 -0.0048 0.0001 0.0000 -0.0000 0.0008 0.243 - 157 0.5610 36.1619 13.5246 -0.1805 0.0215 -0.0084 -0.0050 0.0001 0.0000 0.0001 0.0006 0.266 - 158 0.9350 34.0626 12.7394 -0.1805 0.0136 -0.0130 -0.0053 0.0000 0.0000 0.0003 0.0006 0.311 - 159 1.3090 31.2096 11.6724 -0.1731 -0.0001 -0.0216 -0.0055 0.0000 0.0000 0.0007 0.0005 0.373 - 160 1.6830 26.5957 9.9468 -0.1326 -0.0064 -0.0629 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.411 + 151 -1.6830 26.5957 9.9468 -0.1344 -0.0065 -0.0637 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.413 + 152 -1.3090 31.2096 11.6724 -0.1754 -0.0000 -0.0219 -0.0056 0.0000 0.0000 0.0007 0.0005 0.376 + 153 -0.9350 34.0626 12.7394 -0.1830 0.0138 -0.0131 -0.0054 0.0000 0.0000 0.0003 0.0006 0.314 + 154 -0.5610 36.1619 13.5246 -0.1830 0.0217 -0.0085 -0.0051 0.0001 0.0000 0.0001 0.0006 0.269 + 155 -0.1870 37.5332 14.0374 -0.1821 0.0252 -0.0056 -0.0049 0.0001 0.0000 -0.0000 0.0008 0.246 + 156 0.1870 37.5332 14.0374 -0.1821 0.0252 -0.0056 -0.0049 0.0001 0.0000 -0.0000 0.0008 0.246 + 157 0.5610 36.1619 13.5246 -0.1830 0.0217 -0.0085 -0.0051 0.0001 0.0000 0.0001 0.0006 0.269 + 158 0.9350 34.0626 12.7394 -0.1830 0.0138 -0.0131 -0.0054 0.0000 0.0000 0.0003 0.0006 0.314 + 159 1.3090 31.2096 11.6724 -0.1754 -0.0000 -0.0219 -0.0056 0.0000 0.0000 0.0007 0.0005 0.376 + 160 1.6830 26.5957 9.9468 -0.1344 -0.0065 -0.0637 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.413 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.056 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.702 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.676 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.664 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.658 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.639 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.617 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.575 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.516 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.484 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.911 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.663 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.652 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.645 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.629 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.603 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.588 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.553 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.508 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.471 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_02_03.txt b/regression/scripts/AVL/avl_files/strip_forces_case_02_03.txt index eda88522d7..39f5643d34 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_02_03.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_02_03.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.17252 Clsurf = -0.03137 - CYsurf = -0.01147 Cmsurf = -0.14839 - CDsurf = 0.00313 Cnsurf = 0.00019 - CDisurf = 0.00313 CDvsurf = 0.00000 + CLsurf = 0.17310 Clsurf = -0.03142 + CYsurf = -0.01144 Cmsurf = -0.14871 + CDsurf = 0.00307 Cnsurf = 0.00019 + CDisurf = 0.00307 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.33749 CDsurf = 0.00611 + CLsurf = 0.33861 CDsurf = 0.00599 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 2.4936 0.0842 0.4079 0.3159 0.1700 0.0000 -0.0164 -0.0791 0.302 - 2 0.1025 7.6885 1.0492 2.3803 0.0836 0.3983 0.3085 0.0361 0.0000 -0.0165 -0.0767 0.303 - 3 0.2837 7.5620 1.7073 2.3675 0.0821 0.4032 0.3123 0.0274 0.0000 -0.0153 -0.0764 0.299 - 4 0.5530 7.3741 2.3052 2.3533 0.0794 0.4111 0.3185 0.0243 0.0000 -0.0135 -0.0762 0.292 - 5 0.9075 7.1267 2.8223 2.3265 0.0754 0.4207 0.3259 0.0216 0.0000 -0.0117 -0.0762 0.286 - 6 1.3432 6.8226 3.2414 2.2815 0.0702 0.4311 0.3340 0.0180 0.0000 -0.0101 -0.0766 0.280 - 7 1.8554 6.4651 3.5491 2.2134 0.0643 0.4415 0.3420 0.0158 0.0000 -0.0091 -0.0774 0.277 - 8 2.4386 6.0582 3.7368 2.1175 0.0571 0.4510 0.3493 0.0114 0.0000 -0.0089 -0.0787 0.276 - 9 3.0862 5.6062 3.8005 1.9929 0.0469 0.4588 0.3554 0.0080 0.0000 -0.0096 -0.0805 0.277 - 10 3.7613 5.1351 3.4440 1.8545 0.0361 0.4663 0.3612 0.0055 0.0000 -0.0113 -0.0830 0.281 - 11 4.4532 4.6522 3.3149 1.7042 0.0252 0.4732 0.3665 0.0011 0.0000 -0.0141 -0.0864 0.289 - 12 5.1831 4.1429 3.0930 1.5424 0.0099 0.4811 0.3726 -0.0031 0.0000 -0.0179 -0.0906 0.298 - 13 6.0123 3.7903 3.4706 1.3902 0.0007 0.4484 0.3672 -0.0045 0.0000 -0.0198 -0.0995 0.304 - 14 6.9353 3.6075 3.3775 1.2774 0.0022 0.4329 0.3544 -0.0031 0.0000 -0.0203 -0.0970 0.307 - 15 7.8737 3.4215 3.2389 1.1819 0.0026 0.4223 0.3457 -0.0025 0.0000 -0.0203 -0.0952 0.309 - 16 8.8172 3.2345 3.0619 1.0977 0.0030 0.4148 0.3396 -0.0022 0.0000 -0.0202 -0.0937 0.310 - 17 9.7556 3.0486 2.8543 1.0208 0.0035 0.4093 0.3351 -0.0019 0.0000 -0.0201 -0.0926 0.310 - 18 10.6786 2.8657 2.6240 0.9497 0.0041 0.4051 0.3317 -0.0018 0.0000 -0.0200 -0.0917 0.310 - 19 11.5760 2.6879 2.3787 0.8828 0.0050 0.4015 0.3287 -0.0017 0.0000 -0.0198 -0.0909 0.310 - 20 12.4328 2.5181 2.1010 0.8195 0.0061 0.3978 0.3257 -0.0016 0.0000 -0.0196 -0.0901 0.310 - 21 13.2400 2.3582 1.8520 0.7588 0.0076 0.3933 0.3220 -0.0015 0.0000 -0.0192 -0.0889 0.310 - 22 13.9941 2.2087 1.6074 0.6993 0.0096 0.3870 0.3169 -0.0014 0.0000 -0.0187 -0.0873 0.309 - 23 14.6868 2.0715 1.3716 0.6393 0.0124 0.3772 0.3088 -0.0013 0.0000 -0.0178 -0.0847 0.308 - 24 15.3105 1.9479 1.1479 0.5763 0.0161 0.3616 0.2961 -0.0011 0.0000 -0.0165 -0.0807 0.306 - 25 15.8583 1.8393 0.9381 0.5068 0.0204 0.3368 0.2757 -0.0007 0.0000 -0.0149 -0.0748 0.304 - 26 16.3244 1.7470 0.7427 0.4280 0.0250 0.2994 0.2451 0.0002 0.0000 -0.0145 -0.0676 0.309 - 27 16.6722 1.4928 0.4131 0.3427 0.0300 0.7727 0.2298 -0.0029 0.0000 -0.0133 -0.0335 0.308 - 28 16.9098 1.1466 0.2292 0.2554 0.0376 0.7503 0.2231 -0.0068 0.0000 -0.0038 -0.0283 0.267 - 29 17.0696 0.9138 0.1104 0.1588 0.0443 0.5859 0.1742 -0.0096 0.0000 0.0066 -0.0177 0.212 - 30 17.1499 0.7967 0.0322 0.0540 0.0478 0.2287 0.0680 -0.0067 0.0000 0.0060 -0.0053 0.162 + 1 0.0114 7.7520 0.3539 2.5101 0.0842 0.4106 0.3181 0.1701 0.0000 -0.0178 -0.0807 0.306 + 2 0.1025 7.6885 1.0491 2.3957 0.0837 0.4009 0.3105 0.0360 0.0000 -0.0178 -0.0781 0.307 + 3 0.2837 7.5620 1.7073 2.3830 0.0824 0.4058 0.3144 0.0274 0.0000 -0.0166 -0.0779 0.303 + 4 0.5530 7.3741 2.3052 2.3685 0.0799 0.4138 0.3206 0.0236 0.0000 -0.0148 -0.0777 0.296 + 5 0.9075 7.1267 2.8223 2.3420 0.0760 0.4235 0.3281 0.0213 0.0000 -0.0130 -0.0777 0.290 + 6 1.3432 6.8226 3.2414 2.2966 0.0708 0.4340 0.3362 0.0182 0.0000 -0.0114 -0.0781 0.284 + 7 1.8554 6.4651 3.5491 2.2271 0.0649 0.4444 0.3442 0.0139 0.0000 -0.0103 -0.0788 0.280 + 8 2.4386 6.0582 3.7368 2.1308 0.0577 0.4538 0.3515 0.0117 0.0000 -0.0100 -0.0800 0.278 + 9 3.0862 5.6062 3.8005 2.0079 0.0477 0.4623 0.3581 0.0081 0.0000 -0.0104 -0.0817 0.279 + 10 3.7613 5.1351 3.4440 1.8579 0.0367 0.4672 0.3619 0.0053 0.0000 -0.0121 -0.0838 0.283 + 11 4.4532 4.6522 3.3149 1.7122 0.0251 0.4754 0.3682 0.0012 0.0000 -0.0139 -0.0865 0.288 + 12 5.1831 4.1429 3.0930 1.5447 0.0092 0.4818 0.3732 -0.0031 0.0000 -0.0169 -0.0900 0.295 + 13 6.0123 3.7903 3.4706 1.3927 0.0002 0.4493 0.3678 -0.0045 0.0000 -0.0183 -0.0983 0.300 + 14 6.9353 3.6075 3.3775 1.2794 0.0020 0.4336 0.3550 -0.0031 0.0000 -0.0187 -0.0958 0.303 + 15 7.8737 3.4215 3.2389 1.1837 0.0025 0.4229 0.3463 -0.0025 0.0000 -0.0187 -0.0939 0.304 + 16 8.8172 3.2345 3.0619 1.0991 0.0029 0.4154 0.3401 -0.0022 0.0000 -0.0186 -0.0924 0.305 + 17 9.7556 3.0486 2.8543 1.0221 0.0034 0.4098 0.3355 -0.0020 0.0000 -0.0185 -0.0913 0.305 + 18 10.6786 2.8657 2.6239 0.9507 0.0041 0.4055 0.3320 -0.0018 0.0000 -0.0184 -0.0904 0.305 + 19 11.5760 2.6879 2.3787 0.8837 0.0049 0.4019 0.3290 -0.0017 0.0000 -0.0182 -0.0896 0.305 + 20 12.4328 2.5181 2.1010 0.8203 0.0061 0.3982 0.3260 -0.0016 0.0000 -0.0180 -0.0887 0.305 + 21 13.2400 2.3582 1.8520 0.7595 0.0075 0.3937 0.3223 -0.0016 0.0000 -0.0176 -0.0876 0.305 + 22 13.9941 2.2087 1.6074 0.6998 0.0096 0.3873 0.3171 -0.0015 0.0000 -0.0171 -0.0859 0.304 + 23 14.6868 2.0715 1.3716 0.6396 0.0124 0.3774 0.3090 -0.0013 0.0000 -0.0162 -0.0834 0.302 + 24 15.3105 1.9479 1.1479 0.5764 0.0161 0.3617 0.2961 -0.0011 0.0000 -0.0149 -0.0793 0.300 + 25 15.8583 1.8393 0.9381 0.5068 0.0203 0.3368 0.2757 -0.0007 0.0000 -0.0133 -0.0733 0.298 + 26 16.3244 1.7470 0.7427 0.4275 0.0247 0.2991 0.2449 0.0002 0.0000 -0.0130 -0.0661 0.303 + 27 16.6722 1.4928 0.4131 0.3422 0.0297 0.7718 0.2295 -0.0030 0.0000 -0.0120 -0.0329 0.302 + 28 16.9098 1.1466 0.2292 0.2553 0.0375 0.7499 0.2230 -0.0069 0.0000 -0.0028 -0.0279 0.263 + 29 17.0696 0.9138 0.1104 0.1588 0.0444 0.5859 0.1742 -0.0097 0.0000 0.0072 -0.0174 0.209 + 30 17.1499 0.7967 0.0322 0.0540 0.0485 0.2290 0.0681 -0.0068 0.0000 0.0062 -0.0052 0.159 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.17252 Clsurf = 0.03137 - CYsurf = 0.01147 Cmsurf = -0.14839 - CDsurf = 0.00313 Cnsurf = -0.00019 - CDisurf = 0.00313 CDvsurf = 0.00000 + CLsurf = 0.17310 Clsurf = 0.03142 + CYsurf = 0.01144 Cmsurf = -0.14871 + CDsurf = 0.00307 Cnsurf = -0.00019 + CDisurf = 0.00307 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.33749 CDsurf = 0.00611 + CLsurf = 0.33861 CDsurf = 0.00599 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 2.4936 0.0843 0.4079 0.3159 0.1700 0.0000 -0.0164 0.0791 0.302 - 32 -0.1025 7.6885 1.0492 2.3803 0.0836 0.3983 0.3085 0.0361 0.0000 -0.0165 0.0767 0.303 - 33 -0.2837 7.5620 1.7073 2.3675 0.0821 0.4032 0.3123 0.0274 0.0000 -0.0153 0.0764 0.299 - 34 -0.5530 7.3741 2.3052 2.3533 0.0794 0.4111 0.3185 0.0243 0.0000 -0.0135 0.0762 0.292 - 35 -0.9075 7.1267 2.8223 2.3265 0.0754 0.4207 0.3259 0.0216 0.0000 -0.0117 0.0762 0.286 - 36 -1.3432 6.8226 3.2414 2.2815 0.0702 0.4311 0.3340 0.0180 0.0000 -0.0101 0.0766 0.280 - 37 -1.8554 6.4651 3.5491 2.2134 0.0643 0.4415 0.3420 0.0158 0.0000 -0.0091 0.0774 0.277 - 38 -2.4386 6.0582 3.7368 2.1175 0.0571 0.4510 0.3493 0.0114 0.0000 -0.0089 0.0787 0.276 - 39 -3.0862 5.6062 3.8005 1.9929 0.0469 0.4588 0.3554 0.0080 0.0000 -0.0096 0.0805 0.277 - 40 -3.7613 5.1351 3.4440 1.8545 0.0361 0.4663 0.3612 0.0055 0.0000 -0.0113 0.0830 0.281 - 41 -4.4532 4.6522 3.3149 1.7042 0.0252 0.4732 0.3665 0.0011 0.0000 -0.0141 0.0864 0.289 - 42 -5.1831 4.1429 3.0930 1.5424 0.0099 0.4811 0.3726 -0.0031 0.0000 -0.0179 0.0906 0.298 - 43 -6.0123 3.7903 3.4706 1.3902 0.0007 0.4484 0.3672 -0.0045 0.0000 -0.0198 0.0995 0.304 - 44 -6.9353 3.6075 3.3775 1.2774 0.0022 0.4329 0.3544 -0.0031 0.0000 -0.0203 0.0970 0.307 - 45 -7.8737 3.4215 3.2389 1.1819 0.0026 0.4223 0.3457 -0.0025 0.0000 -0.0203 0.0952 0.309 - 46 -8.8172 3.2345 3.0619 1.0976 0.0030 0.4148 0.3396 -0.0022 0.0000 -0.0202 0.0937 0.310 - 47 -9.7556 3.0486 2.8543 1.0208 0.0035 0.4093 0.3351 -0.0019 0.0000 -0.0201 0.0926 0.310 - 48 -10.6786 2.8657 2.6240 0.9497 0.0041 0.4051 0.3316 -0.0018 0.0000 -0.0200 0.0917 0.310 - 49 -11.5760 2.6879 2.3787 0.8828 0.0050 0.4015 0.3287 -0.0017 0.0000 -0.0198 0.0909 0.310 - 50 -12.4328 2.5181 2.1010 0.8195 0.0061 0.3978 0.3257 -0.0016 0.0000 -0.0196 0.0901 0.310 - 51 -13.2400 2.3582 1.8520 0.7588 0.0076 0.3933 0.3220 -0.0015 0.0000 -0.0192 0.0889 0.310 - 52 -13.9941 2.2087 1.6074 0.6993 0.0096 0.3870 0.3169 -0.0014 0.0000 -0.0187 0.0873 0.309 - 53 -14.6868 2.0715 1.3716 0.6393 0.0124 0.3772 0.3088 -0.0013 0.0000 -0.0178 0.0847 0.308 - 54 -15.3105 1.9479 1.1479 0.5762 0.0161 0.3616 0.2961 -0.0011 0.0000 -0.0165 0.0807 0.306 - 55 -15.8583 1.8393 0.9381 0.5068 0.0204 0.3368 0.2757 -0.0007 0.0000 -0.0149 0.0748 0.304 - 56 -16.3244 1.7470 0.7427 0.4280 0.0250 0.2994 0.2451 0.0002 0.0000 -0.0145 0.0676 0.309 - 57 -16.6722 1.4928 0.4131 0.3427 0.0300 0.7727 0.2298 -0.0029 0.0000 -0.0133 0.0335 0.308 - 58 -16.9098 1.1466 0.2292 0.2554 0.0376 0.7503 0.2231 -0.0068 0.0000 -0.0038 0.0283 0.267 - 59 -17.0696 0.9138 0.1104 0.1588 0.0443 0.5859 0.1742 -0.0096 0.0000 0.0066 0.0177 0.212 - 60 -17.1499 0.7967 0.0322 0.0540 0.0478 0.2287 0.0680 -0.0067 0.0000 0.0060 0.0053 0.162 + 31 -0.0114 7.7520 0.3539 2.5101 0.0842 0.4106 0.3181 0.1701 0.0000 -0.0178 0.0807 0.306 + 32 -0.1025 7.6885 1.0491 2.3957 0.0837 0.4009 0.3105 0.0360 0.0000 -0.0178 0.0781 0.307 + 33 -0.2837 7.5620 1.7073 2.3830 0.0824 0.4058 0.3144 0.0274 0.0000 -0.0166 0.0779 0.303 + 34 -0.5530 7.3741 2.3052 2.3685 0.0799 0.4138 0.3206 0.0236 0.0000 -0.0148 0.0777 0.296 + 35 -0.9075 7.1267 2.8223 2.3420 0.0760 0.4235 0.3281 0.0213 0.0000 -0.0130 0.0777 0.290 + 36 -1.3432 6.8226 3.2414 2.2966 0.0708 0.4340 0.3362 0.0182 0.0000 -0.0114 0.0781 0.284 + 37 -1.8554 6.4651 3.5491 2.2271 0.0649 0.4444 0.3442 0.0139 0.0000 -0.0103 0.0788 0.280 + 38 -2.4386 6.0582 3.7368 2.1308 0.0577 0.4538 0.3515 0.0117 0.0000 -0.0100 0.0800 0.278 + 39 -3.0862 5.6062 3.8005 2.0079 0.0477 0.4623 0.3581 0.0081 0.0000 -0.0104 0.0817 0.279 + 40 -3.7613 5.1351 3.4440 1.8579 0.0367 0.4672 0.3619 0.0053 0.0000 -0.0121 0.0838 0.283 + 41 -4.4532 4.6522 3.3149 1.7122 0.0251 0.4754 0.3682 0.0012 0.0000 -0.0139 0.0865 0.288 + 42 -5.1831 4.1429 3.0930 1.5447 0.0092 0.4818 0.3732 -0.0031 0.0000 -0.0169 0.0900 0.295 + 43 -6.0123 3.7903 3.4706 1.3927 0.0002 0.4493 0.3678 -0.0045 0.0000 -0.0183 0.0983 0.300 + 44 -6.9353 3.6075 3.3775 1.2794 0.0020 0.4336 0.3550 -0.0031 0.0000 -0.0187 0.0958 0.303 + 45 -7.8737 3.4215 3.2389 1.1837 0.0025 0.4229 0.3462 -0.0025 0.0000 -0.0187 0.0939 0.304 + 46 -8.8172 3.2345 3.0619 1.0991 0.0029 0.4154 0.3401 -0.0022 0.0000 -0.0186 0.0924 0.305 + 47 -9.7556 3.0486 2.8543 1.0221 0.0034 0.4098 0.3355 -0.0020 0.0000 -0.0185 0.0913 0.305 + 48 -10.6786 2.8657 2.6239 0.9507 0.0041 0.4055 0.3320 -0.0018 0.0000 -0.0184 0.0904 0.305 + 49 -11.5760 2.6879 2.3787 0.8837 0.0049 0.4019 0.3290 -0.0017 0.0000 -0.0182 0.0896 0.305 + 50 -12.4328 2.5181 2.1010 0.8203 0.0061 0.3982 0.3260 -0.0016 0.0000 -0.0180 0.0887 0.305 + 51 -13.2400 2.3582 1.8520 0.7595 0.0075 0.3937 0.3223 -0.0016 0.0000 -0.0176 0.0876 0.305 + 52 -13.9941 2.2087 1.6074 0.6998 0.0096 0.3873 0.3171 -0.0015 0.0000 -0.0171 0.0859 0.304 + 53 -14.6868 2.0715 1.3716 0.6396 0.0124 0.3774 0.3090 -0.0013 0.0000 -0.0162 0.0834 0.302 + 54 -15.3105 1.9479 1.1479 0.5764 0.0161 0.3617 0.2961 -0.0011 0.0000 -0.0149 0.0793 0.300 + 55 -15.8583 1.8393 0.9381 0.5068 0.0203 0.3368 0.2757 -0.0007 0.0000 -0.0133 0.0733 0.298 + 56 -16.3244 1.7470 0.7427 0.4275 0.0247 0.2991 0.2449 0.0002 0.0000 -0.0130 0.0661 0.303 + 57 -16.6722 1.4928 0.4131 0.3422 0.0297 0.7718 0.2295 -0.0030 0.0000 -0.0120 0.0329 0.302 + 58 -16.9098 1.1466 0.2292 0.2553 0.0375 0.7499 0.2230 -0.0069 0.0000 -0.0028 0.0279 0.263 + 59 -17.0696 0.9138 0.1104 0.1588 0.0444 0.5859 0.1742 -0.0097 0.0000 0.0072 0.0174 0.209 + 60 -17.1499 0.7967 0.0322 0.0540 0.0485 0.2290 0.0681 -0.0068 0.0000 0.0062 0.0052 0.159 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00304 Clsurf = -0.00046 - CYsurf = -0.00048 Cmsurf = -0.01543 - CDsurf = 0.00008 Cnsurf = 0.00029 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00291 Clsurf = -0.00045 + CYsurf = -0.00046 Cmsurf = -0.01480 + CDsurf = 0.00008 Cnsurf = 0.00028 CDisurf = 0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01851 CDsurf = 0.00050 + CLsurf = 0.01771 CDsurf = 0.00048 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.0054 0.0425 0.0016 0.0013 0.0001 0.0000 -0.0011 -0.0012 1.144 - 62 0.0418 4.2566 0.2392 0.0054 0.0425 0.0016 0.0013 0.0000 0.0000 -0.0011 -0.0012 1.147 - 63 0.1156 4.2274 0.3930 0.0054 0.0423 0.0017 0.0013 0.0000 0.0000 -0.0011 -0.0012 1.135 - 64 0.2254 4.1839 0.5386 0.0056 0.0419 0.0017 0.0013 0.0000 0.0000 -0.0011 -0.0012 1.103 - 65 0.3698 4.1268 0.6730 0.0060 0.0414 0.0019 0.0015 0.0000 0.0000 -0.0012 -0.0013 1.043 - 66 0.5474 4.0565 0.7936 0.0067 0.0406 0.0021 0.0016 0.0001 0.0000 -0.0012 -0.0013 0.956 - 67 0.7617 3.9717 0.9441 0.0078 0.0396 0.0025 0.0020 0.0001 0.0000 -0.0012 -0.0014 0.848 - 68 1.0116 3.8728 1.0344 0.0095 0.0384 0.0032 0.0025 0.0001 0.0000 -0.0012 -0.0015 0.731 - 69 1.2891 3.7630 1.1046 0.0121 0.0370 0.0042 0.0032 0.0001 0.0000 -0.0012 -0.0017 0.620 - 70 1.5912 3.6435 1.1542 0.0158 0.0356 0.0056 0.0043 0.0001 0.0000 -0.0012 -0.0019 0.526 - 71 1.9146 3.5155 1.1831 0.0208 0.0341 0.0077 0.0059 0.0002 0.0000 -0.0012 -0.0023 0.452 - 72 2.2558 3.3805 1.1921 0.0271 0.0326 0.0104 0.0080 0.0003 0.0000 -0.0012 -0.0027 0.395 - 73 2.6109 3.2400 1.1821 0.0347 0.0313 0.0139 0.0107 0.0004 0.0000 -0.0011 -0.0032 0.353 - 74 2.9762 3.0955 1.1548 0.0435 0.0300 0.0182 0.0140 0.0005 0.0000 -0.0010 -0.0039 0.323 - 75 3.3476 2.9485 1.1122 0.0530 0.0288 0.0233 0.0180 0.0006 0.0000 -0.0009 -0.0046 0.300 - 76 3.7210 2.8008 1.0564 0.0627 0.0278 0.0290 0.0224 0.0007 0.0000 -0.0008 -0.0054 0.284 - 77 4.0924 2.6538 0.9900 0.0722 0.0269 0.0353 0.0272 0.0008 0.0000 -0.0006 -0.0063 0.271 - 78 4.4577 2.5093 0.9155 0.0809 0.0263 0.0418 0.0322 0.0009 0.0000 -0.0004 -0.0072 0.261 - 79 4.8128 2.3687 0.8353 0.0882 0.0259 0.0483 0.0372 0.0010 0.0000 -0.0001 -0.0080 0.253 - 80 5.1540 2.2338 0.7518 0.0938 0.0256 0.0544 0.0420 0.0011 0.0000 0.0002 -0.0088 0.245 - 81 5.4774 2.1058 0.6671 0.0972 0.0256 0.0598 0.0461 0.0012 0.0000 0.0005 -0.0094 0.238 - 82 5.7795 1.9862 0.5830 0.0982 0.0258 0.0641 0.0494 0.0012 0.0000 0.0010 -0.0097 0.230 - 83 6.0570 1.8764 0.5012 0.0967 0.0261 0.0668 0.0515 0.0012 0.0000 0.0015 -0.0097 0.221 - 84 6.3069 1.7776 0.4225 0.0926 0.0266 0.0676 0.0521 0.0011 0.0000 0.0021 -0.0094 0.211 - 85 6.5264 1.6907 0.3478 0.0859 0.0271 0.0659 0.0508 0.0011 0.0000 0.0027 -0.0086 0.198 - 86 6.7314 1.6096 0.3326 0.0764 0.0276 0.0615 0.0474 0.0009 0.0000 0.0033 -0.0074 0.181 - 87 6.9144 1.5372 0.2507 0.0631 0.0282 0.0532 0.0410 0.0007 0.0000 0.0036 -0.0057 0.161 - 88 7.0535 1.4822 0.1746 0.0471 0.0286 0.0412 0.0318 0.0005 0.0000 0.0035 -0.0038 0.140 - 89 7.1471 1.4451 0.1029 0.0291 0.0289 0.0261 0.0201 0.0003 0.0000 0.0026 -0.0021 0.121 + 61 0.0047 4.2713 0.0803 0.0014 0.0426 0.0004 0.0003 0.0000 0.0000 -0.0011 -0.0010 + 62 0.0418 4.2566 0.2392 0.0014 0.0426 0.0004 0.0003 0.0000 0.0000 -0.0011 -0.0010 + 63 0.1156 4.2274 0.3930 0.0015 0.0424 0.0005 0.0003 0.0000 0.0000 -0.0011 -0.0010 + 64 0.2254 4.1839 0.5386 0.0017 0.0420 0.0005 0.0004 0.0000 0.0000 -0.0011 -0.0010 + 65 0.3698 4.1268 0.6730 0.0020 0.0415 0.0006 0.0005 0.0000 0.0000 -0.0011 -0.0011 + 66 0.5474 4.0565 0.7936 0.0027 0.0407 0.0009 0.0007 0.0000 0.0000 -0.0011 -0.0011 1.960 + 67 0.7617 3.9717 0.9441 0.0039 0.0397 0.0013 0.0010 0.0000 0.0000 -0.0012 -0.0012 1.448 + 68 1.0116 3.8728 1.0344 0.0057 0.0385 0.0019 0.0015 0.0000 0.0000 -0.0012 -0.0013 1.058 + 69 1.2891 3.7630 1.1046 0.0084 0.0371 0.0029 0.0022 0.0001 0.0000 -0.0012 -0.0015 0.790 + 70 1.5912 3.6435 1.1542 0.0122 0.0357 0.0043 0.0033 0.0001 0.0000 -0.0012 -0.0017 0.612 + 71 1.9146 3.5155 1.1831 0.0173 0.0342 0.0064 0.0049 0.0002 0.0000 -0.0012 -0.0021 0.495 + 72 2.2558 3.3805 1.1921 0.0238 0.0328 0.0091 0.0070 0.0002 0.0000 -0.0012 -0.0025 0.418 + 73 2.6109 3.2400 1.1821 0.0316 0.0314 0.0126 0.0097 0.0003 0.0000 -0.0011 -0.0030 0.365 + 74 2.9762 3.0955 1.1548 0.0406 0.0301 0.0170 0.0131 0.0004 0.0000 -0.0010 -0.0037 0.329 + 75 3.3476 2.9485 1.1122 0.0503 0.0289 0.0221 0.0171 0.0006 0.0000 -0.0009 -0.0044 0.304 + 76 3.7210 2.8008 1.0564 0.0604 0.0279 0.0280 0.0216 0.0007 0.0000 -0.0008 -0.0052 0.286 + 77 4.0924 2.6538 0.9900 0.0702 0.0270 0.0343 0.0264 0.0008 0.0000 -0.0006 -0.0061 0.272 + 78 4.4577 2.5093 0.9155 0.0792 0.0264 0.0409 0.0315 0.0009 0.0000 -0.0004 -0.0070 0.262 + 79 4.8128 2.3687 0.8353 0.0868 0.0259 0.0475 0.0366 0.0010 0.0000 -0.0001 -0.0079 0.253 + 80 5.1540 2.2338 0.7518 0.0926 0.0257 0.0537 0.0414 0.0011 0.0000 0.0002 -0.0087 0.246 + 81 5.4774 2.1058 0.6671 0.0962 0.0257 0.0592 0.0457 0.0012 0.0000 0.0005 -0.0093 0.238 + 82 5.7795 1.9862 0.5830 0.0974 0.0258 0.0636 0.0490 0.0012 0.0000 0.0010 -0.0096 0.230 + 83 6.0570 1.8764 0.5012 0.0960 0.0261 0.0663 0.0512 0.0012 0.0000 0.0015 -0.0097 0.221 + 84 6.3069 1.7776 0.4225 0.0921 0.0266 0.0671 0.0518 0.0011 0.0000 0.0020 -0.0093 0.211 + 85 6.5264 1.6907 0.3478 0.0855 0.0271 0.0656 0.0506 0.0011 0.0000 0.0027 -0.0085 0.197 + 86 6.7314 1.6096 0.3326 0.0760 0.0276 0.0612 0.0472 0.0009 0.0000 0.0033 -0.0073 0.181 + 87 6.9144 1.5372 0.2507 0.0628 0.0282 0.0530 0.0409 0.0007 0.0000 0.0036 -0.0056 0.161 + 88 7.0535 1.4822 0.1746 0.0469 0.0286 0.0410 0.0316 0.0005 0.0000 0.0035 -0.0038 0.140 + 89 7.1471 1.4451 0.1029 0.0290 0.0289 0.0260 0.0200 0.0003 0.0000 0.0026 -0.0021 0.121 90 7.1941 1.4265 0.0340 0.0098 0.0291 0.0089 0.0069 0.0000 0.0000 0.0010 -0.0007 0.110 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00304 Clsurf = 0.00046 - CYsurf = 0.00048 Cmsurf = -0.01543 - CDsurf = 0.00008 Cnsurf = -0.00029 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00291 Clsurf = 0.00045 + CYsurf = 0.00046 Cmsurf = -0.01480 + CDsurf = 0.00008 Cnsurf = -0.00028 CDisurf = 0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01851 CDsurf = 0.00050 + CLsurf = 0.01771 CDsurf = 0.00048 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.0054 0.0425 0.0016 0.0013 0.0001 0.0000 -0.0011 0.0012 1.144 - 92 -0.0418 4.2566 0.2392 0.0054 0.0425 0.0016 0.0013 0.0000 0.0000 -0.0011 0.0012 1.146 - 93 -0.1156 4.2274 0.3930 0.0054 0.0423 0.0017 0.0013 0.0000 0.0000 -0.0011 0.0012 1.135 - 94 -0.2254 4.1839 0.5386 0.0056 0.0419 0.0017 0.0013 0.0000 0.0000 -0.0011 0.0012 1.103 - 95 -0.3698 4.1268 0.6730 0.0060 0.0414 0.0019 0.0015 0.0000 0.0000 -0.0012 0.0013 1.043 - 96 -0.5474 4.0565 0.7936 0.0067 0.0406 0.0021 0.0016 0.0001 0.0000 -0.0012 0.0013 0.956 - 97 -0.7617 3.9717 0.9441 0.0078 0.0396 0.0025 0.0020 0.0001 0.0000 -0.0012 0.0014 0.848 - 98 -1.0116 3.8728 1.0344 0.0095 0.0384 0.0032 0.0025 0.0001 0.0000 -0.0012 0.0015 0.731 - 99 -1.2891 3.7630 1.1046 0.0121 0.0370 0.0042 0.0032 0.0001 0.0000 -0.0012 0.0017 0.620 - 100 -1.5912 3.6435 1.1542 0.0158 0.0356 0.0056 0.0043 0.0001 0.0000 -0.0012 0.0019 0.526 - 101 -1.9146 3.5155 1.1831 0.0208 0.0341 0.0077 0.0059 0.0002 0.0000 -0.0012 0.0023 0.451 - 102 -2.2558 3.3805 1.1921 0.0271 0.0326 0.0104 0.0080 0.0003 0.0000 -0.0012 0.0027 0.395 - 103 -2.6109 3.2400 1.1821 0.0347 0.0313 0.0139 0.0107 0.0004 0.0000 -0.0011 0.0032 0.353 - 104 -2.9762 3.0955 1.1548 0.0435 0.0300 0.0182 0.0140 0.0005 0.0000 -0.0010 0.0039 0.323 - 105 -3.3476 2.9485 1.1122 0.0530 0.0288 0.0233 0.0180 0.0006 0.0000 -0.0009 0.0046 0.300 - 106 -3.7210 2.8008 1.0564 0.0627 0.0278 0.0290 0.0224 0.0007 0.0000 -0.0008 0.0054 0.284 - 107 -4.0924 2.6538 0.9900 0.0722 0.0269 0.0353 0.0272 0.0008 0.0000 -0.0006 0.0063 0.271 - 108 -4.4577 2.5093 0.9155 0.0809 0.0263 0.0418 0.0322 0.0009 0.0000 -0.0004 0.0072 0.261 - 109 -4.8128 2.3687 0.8353 0.0882 0.0258 0.0483 0.0372 0.0010 0.0000 -0.0001 0.0080 0.253 - 110 -5.1540 2.2338 0.7518 0.0938 0.0256 0.0544 0.0420 0.0011 0.0000 0.0002 0.0088 0.245 - 111 -5.4774 2.1058 0.6671 0.0972 0.0256 0.0598 0.0461 0.0012 0.0000 0.0005 0.0094 0.238 - 112 -5.7795 1.9862 0.5830 0.0982 0.0258 0.0641 0.0494 0.0012 0.0000 0.0010 0.0097 0.230 - 113 -6.0570 1.8764 0.5012 0.0967 0.0261 0.0668 0.0515 0.0012 0.0000 0.0015 0.0097 0.221 - 114 -6.3069 1.7776 0.4225 0.0926 0.0266 0.0676 0.0521 0.0011 0.0000 0.0021 0.0094 0.211 - 115 -6.5264 1.6907 0.3478 0.0859 0.0271 0.0659 0.0508 0.0011 0.0000 0.0027 0.0086 0.198 - 116 -6.7314 1.6096 0.3326 0.0764 0.0276 0.0615 0.0474 0.0009 0.0000 0.0033 0.0074 0.181 - 117 -6.9144 1.5372 0.2507 0.0631 0.0282 0.0532 0.0410 0.0007 0.0000 0.0036 0.0057 0.161 - 118 -7.0535 1.4822 0.1746 0.0471 0.0286 0.0412 0.0318 0.0005 0.0000 0.0035 0.0038 0.140 - 119 -7.1471 1.4451 0.1029 0.0291 0.0289 0.0261 0.0201 0.0003 0.0000 0.0026 0.0021 0.121 + 91 -0.0047 4.2713 0.0803 0.0014 0.0426 0.0004 0.0003 0.0000 0.0000 -0.0011 0.0010 + 92 -0.0418 4.2566 0.2392 0.0014 0.0426 0.0004 0.0003 0.0000 0.0000 -0.0011 0.0010 + 93 -0.1156 4.2274 0.3930 0.0015 0.0424 0.0005 0.0003 0.0000 0.0000 -0.0011 0.0010 + 94 -0.2254 4.1839 0.5386 0.0017 0.0420 0.0005 0.0004 0.0000 0.0000 -0.0011 0.0010 + 95 -0.3698 4.1268 0.6730 0.0020 0.0415 0.0006 0.0005 0.0000 0.0000 -0.0011 0.0011 + 96 -0.5474 4.0565 0.7936 0.0027 0.0407 0.0009 0.0007 0.0000 0.0000 -0.0011 0.0011 1.960 + 97 -0.7617 3.9717 0.9441 0.0039 0.0397 0.0013 0.0010 0.0000 0.0000 -0.0012 0.0012 1.448 + 98 -1.0116 3.8728 1.0344 0.0057 0.0385 0.0019 0.0015 0.0000 0.0000 -0.0012 0.0013 1.057 + 99 -1.2891 3.7630 1.1046 0.0084 0.0371 0.0029 0.0022 0.0001 0.0000 -0.0012 0.0015 0.790 + 100 -1.5912 3.6435 1.1542 0.0122 0.0357 0.0043 0.0033 0.0001 0.0000 -0.0012 0.0017 0.612 + 101 -1.9146 3.5155 1.1831 0.0173 0.0342 0.0064 0.0049 0.0002 0.0000 -0.0012 0.0021 0.495 + 102 -2.2558 3.3805 1.1921 0.0238 0.0328 0.0091 0.0070 0.0002 0.0000 -0.0012 0.0025 0.418 + 103 -2.6109 3.2400 1.1821 0.0316 0.0314 0.0126 0.0097 0.0003 0.0000 -0.0011 0.0030 0.365 + 104 -2.9762 3.0955 1.1548 0.0406 0.0301 0.0170 0.0131 0.0004 0.0000 -0.0010 0.0037 0.329 + 105 -3.3476 2.9485 1.1122 0.0503 0.0289 0.0221 0.0171 0.0006 0.0000 -0.0009 0.0044 0.304 + 106 -3.7210 2.8008 1.0564 0.0604 0.0279 0.0280 0.0216 0.0007 0.0000 -0.0008 0.0052 0.286 + 107 -4.0924 2.6538 0.9900 0.0702 0.0270 0.0343 0.0264 0.0008 0.0000 -0.0006 0.0061 0.272 + 108 -4.4577 2.5093 0.9155 0.0792 0.0264 0.0409 0.0315 0.0009 0.0000 -0.0004 0.0070 0.262 + 109 -4.8128 2.3687 0.8353 0.0868 0.0259 0.0475 0.0366 0.0010 0.0000 -0.0001 0.0079 0.253 + 110 -5.1540 2.2338 0.7518 0.0926 0.0257 0.0537 0.0414 0.0011 0.0000 0.0002 0.0087 0.246 + 111 -5.4774 2.1058 0.6671 0.0962 0.0257 0.0592 0.0457 0.0012 0.0000 0.0005 0.0093 0.238 + 112 -5.7795 1.9862 0.5830 0.0974 0.0258 0.0636 0.0490 0.0012 0.0000 0.0010 0.0096 0.230 + 113 -6.0570 1.8764 0.5012 0.0960 0.0261 0.0663 0.0512 0.0012 0.0000 0.0015 0.0097 0.221 + 114 -6.3069 1.7776 0.4225 0.0921 0.0266 0.0671 0.0518 0.0011 0.0000 0.0020 0.0093 0.211 + 115 -6.5264 1.6907 0.3478 0.0855 0.0271 0.0656 0.0506 0.0011 0.0000 0.0027 0.0085 0.197 + 116 -6.7314 1.6096 0.3326 0.0760 0.0276 0.0612 0.0472 0.0009 0.0000 0.0033 0.0073 0.181 + 117 -6.9144 1.5372 0.2507 0.0628 0.0282 0.0530 0.0409 0.0007 0.0000 0.0036 0.0056 0.161 + 118 -7.0535 1.4822 0.1746 0.0469 0.0286 0.0410 0.0316 0.0005 0.0000 0.0035 0.0038 0.140 + 119 -7.1471 1.4451 0.1029 0.0290 0.0289 0.0260 0.0200 0.0003 0.0000 0.0026 0.0021 0.121 120 -7.1941 1.4265 0.0340 0.0098 0.0291 0.0089 0.0069 0.0000 0.0000 0.0010 0.0007 0.110 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.213 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.215 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.210 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.210 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.207 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.192 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.174 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.155 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.134 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.118 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.254 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.248 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.260 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.258 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.251 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 + 130 0.0000 4.9969 1.9773 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.208 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.210 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.187 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.171 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.147 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.123 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.116 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00045 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.01671 + CLsurf = -0.00052 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.01678 CDsurf = -0.00012 Cnsurf = -0.00000 CDisurf = -0.00012 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00046 CDsurf = -0.00012 + CLsurf = -0.00053 CDsurf = -0.00012 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.0228 0.0466 -0.0104 -0.0008 -0.0006 0.0000 0.0020 0.0003 - 152 -1.3090 31.2096 11.6724 -0.0208 0.0549 -0.0026 -0.0007 -0.0002 0.0000 0.0022 0.0006 - 153 -0.9350 34.0626 12.7394 -0.0155 0.0605 -0.0011 -0.0005 -0.0001 0.0000 0.0023 0.0008 - 154 -0.5610 36.1619 13.5246 -0.0102 0.0647 -0.0005 -0.0003 0.0000 0.0000 0.0022 0.0010 - 155 -0.1870 37.5332 14.0374 -0.0069 0.0672 -0.0002 -0.0002 0.0001 0.0000 0.0022 0.0016 - 156 0.1870 37.5332 14.0374 -0.0069 0.0672 -0.0002 -0.0002 0.0001 0.0000 0.0022 0.0016 - 157 0.5610 36.1619 13.5246 -0.0102 0.0647 -0.0005 -0.0003 0.0000 0.0000 0.0022 0.0010 - 158 0.9350 34.0626 12.7394 -0.0155 0.0605 -0.0011 -0.0005 -0.0001 0.0000 0.0023 0.0008 - 159 1.3090 31.2096 11.6724 -0.0208 0.0549 -0.0026 -0.0007 -0.0002 0.0000 0.0022 0.0006 - 160 1.6830 26.5957 9.9468 -0.0228 0.0466 -0.0104 -0.0008 -0.0006 0.0000 0.0020 0.0003 + 151 -1.6830 26.5957 9.9468 -0.0246 0.0466 -0.0112 -0.0009 -0.0006 0.0000 0.0020 0.0003 + 152 -1.3090 31.2096 11.6724 -0.0232 0.0549 -0.0029 -0.0007 -0.0002 0.0000 0.0022 0.0006 + 153 -0.9350 34.0626 12.7394 -0.0180 0.0607 -0.0013 -0.0005 -0.0001 0.0000 0.0023 0.0008 + 154 -0.5610 36.1619 13.5246 -0.0127 0.0649 -0.0006 -0.0004 0.0000 0.0000 0.0023 0.0010 + 155 -0.1870 37.5332 14.0374 -0.0094 0.0675 -0.0003 -0.0003 0.0001 0.0000 0.0022 0.0016 + 156 0.1870 37.5332 14.0374 -0.0094 0.0675 -0.0003 -0.0003 0.0001 0.0000 0.0022 0.0016 + 157 0.5610 36.1619 13.5246 -0.0127 0.0649 -0.0006 -0.0004 0.0000 0.0000 0.0023 0.0010 + 158 0.9350 34.0626 12.7394 -0.0180 0.0607 -0.0013 -0.0005 -0.0001 0.0000 0.0023 0.0008 + 159 1.3090 31.2096 11.6724 -0.0232 0.0549 -0.0029 -0.0007 -0.0002 0.0000 0.0022 0.0006 + 160 1.6830 26.5957 9.9468 -0.0246 0.0466 -0.0112 -0.0009 -0.0006 0.0000 0.0020 0.0003 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 0.166 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.439 - 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.460 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.472 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.491 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.529 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.542 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.544 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.545 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.587 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.163 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.406 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.437 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.444 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.451 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.488 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.523 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.545 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.553 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.582 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_02_04.txt b/regression/scripts/AVL/avl_files/strip_forces_case_02_04.txt index 715c6fdc0e..9ce3b8110f 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_02_04.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_02_04.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.29471 Clsurf = -0.05650 - CYsurf = -0.01758 Cmsurf = -0.26179 - CDsurf = 0.00799 Cnsurf = -0.00307 - CDisurf = 0.00799 CDvsurf = 0.00000 + CLsurf = 0.29524 Clsurf = -0.05655 + CYsurf = -0.01747 Cmsurf = -0.26208 + CDsurf = 0.00782 Cnsurf = -0.00308 + CDisurf = 0.00782 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.57624 CDsurf = 0.01559 + CLsurf = 0.57727 CDsurf = 0.01525 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 3.8928 0.1379 0.6071 0.4700 0.3888 0.0000 -0.0254 -0.1237 0.304 - 2 0.1025 7.6885 1.0492 3.6308 0.1375 0.6034 0.4671 0.0792 0.0000 -0.0256 -0.1178 0.305 - 3 0.2837 7.5620 1.7073 3.6065 0.1360 0.6117 0.4735 0.0596 0.0000 -0.0237 -0.1172 0.300 - 4 0.5530 7.3741 2.3052 3.5885 0.1332 0.6250 0.4839 0.0530 0.0000 -0.0209 -0.1169 0.293 - 5 0.9075 7.1267 2.8223 3.5569 0.1280 0.6418 0.4968 0.0477 0.0000 -0.0178 -0.1170 0.286 - 6 1.3432 6.8226 3.2414 3.5047 0.1183 0.6615 0.5121 0.0405 0.0000 -0.0151 -0.1178 0.280 - 7 1.8554 6.4651 3.5491 3.4258 0.1006 0.6829 0.5287 0.0367 0.0000 -0.0131 -0.1195 0.275 - 8 2.4386 6.0582 3.7368 3.3125 0.0825 0.7058 0.5464 0.0277 0.0000 -0.0122 -0.1222 0.272 - 9 3.0862 5.6062 3.8005 3.1628 0.0702 0.7291 0.5644 0.0213 0.0000 -0.0123 -0.1259 0.272 - 10 3.7613 5.1351 3.4440 2.9988 0.0588 0.7554 0.5847 0.0169 0.0000 -0.0135 -0.1309 0.273 - 11 4.4532 4.6522 3.3149 2.8163 0.0460 0.7842 0.6070 0.0074 0.0000 -0.0161 -0.1374 0.277 - 12 5.1831 4.1429 3.0930 2.6153 0.0269 0.8188 0.6338 -0.0016 0.0000 -0.0192 -0.1452 0.280 - 13 6.0123 3.7903 3.4706 2.4144 0.0145 0.7842 0.6399 -0.0053 0.0000 -0.0190 -0.1602 0.280 - 14 6.9353 3.6075 3.3775 2.2617 0.0141 0.7716 0.6296 -0.0032 0.0000 -0.0194 -0.1582 0.281 - 15 7.8737 3.4215 3.2389 2.1263 0.0121 0.7647 0.6240 -0.0026 0.0000 -0.0193 -0.1570 0.281 - 16 8.8172 3.2345 3.0619 2.0010 0.0109 0.7613 0.6212 -0.0025 0.0000 -0.0192 -0.1562 0.281 - 17 9.7556 3.0486 2.8543 1.8813 0.0109 0.7594 0.6197 -0.0026 0.0000 -0.0190 -0.1557 0.281 - 18 10.6786 2.8657 2.6240 1.7660 0.0117 0.7584 0.6188 -0.0026 0.0000 -0.0188 -0.1553 0.280 - 19 11.5760 2.6879 2.3787 1.6539 0.0131 0.7572 0.6179 -0.0028 0.0000 -0.0185 -0.1548 0.280 - 20 12.4328 2.5181 2.1010 1.5447 0.0151 0.7549 0.6160 -0.0030 0.0000 -0.0181 -0.1540 0.279 - 21 13.2400 2.3582 1.8520 1.4372 0.0178 0.7500 0.6120 -0.0031 0.0000 -0.0174 -0.1526 0.278 - 22 13.9941 2.2087 1.6074 1.3293 0.0216 0.7407 0.6044 -0.0031 0.0000 -0.0163 -0.1499 0.277 - 23 14.6868 2.0715 1.3716 1.2183 0.0269 0.7238 0.5906 -0.0029 0.0000 -0.0147 -0.1453 0.275 - 24 15.3105 1.9479 1.1479 1.0996 0.0337 0.6947 0.5669 -0.0025 0.0000 -0.0122 -0.1378 0.272 - 25 15.8583 1.8393 0.9381 0.9669 0.0416 0.6468 0.5278 -0.0014 0.0000 -0.0095 -0.1267 0.268 - 26 16.3244 1.7470 0.7427 0.8151 0.0496 0.5737 0.4682 0.0022 0.0000 -0.0102 -0.1140 0.272 - 27 16.6722 1.4928 0.4131 0.6506 0.0582 1.4751 0.4385 -0.0113 0.0000 -0.0110 -0.0585 0.275 - 28 16.9098 1.1466 0.2292 0.4829 0.0704 1.4298 0.4250 -0.0262 0.0000 0.0063 -0.0488 0.235 - 29 17.0696 0.9138 0.1104 0.2989 0.0807 1.1157 0.3316 -0.0376 0.0000 0.0234 -0.0293 0.179 - 30 17.1499 0.7967 0.0322 0.1013 0.0860 0.4376 0.1301 -0.0276 0.0000 0.0161 -0.0082 0.126 + 1 0.0114 7.7520 0.3539 3.9098 0.1379 0.6100 0.4722 0.3892 0.0000 -0.0269 -0.1254 0.307 + 2 0.1025 7.6885 1.0491 3.6461 0.1375 0.6060 0.4691 0.0791 0.0000 -0.0269 -0.1192 0.307 + 3 0.2837 7.5620 1.7073 3.6219 0.1363 0.6143 0.4756 0.0595 0.0000 -0.0250 -0.1187 0.303 + 4 0.5530 7.3741 2.3052 3.6028 0.1337 0.6277 0.4859 0.0514 0.0000 -0.0222 -0.1184 0.296 + 5 0.9075 7.1267 2.8223 3.5720 0.1286 0.6446 0.4990 0.0469 0.0000 -0.0191 -0.1185 0.288 + 6 1.3432 6.8226 3.2414 3.5192 0.1189 0.6642 0.5142 0.0408 0.0000 -0.0164 -0.1193 0.282 + 7 1.8554 6.4651 3.5491 3.4379 0.1013 0.6859 0.5310 0.0320 0.0000 -0.0144 -0.1209 0.277 + 8 2.4386 6.0582 3.7368 3.3248 0.0831 0.7084 0.5484 0.0282 0.0000 -0.0132 -0.1235 0.274 + 9 3.0862 5.6062 3.8005 3.1806 0.0711 0.7332 0.5676 0.0214 0.0000 -0.0131 -0.1272 0.273 + 10 3.7613 5.1351 3.4440 2.9929 0.0594 0.7540 0.5837 0.0161 0.0000 -0.0147 -0.1317 0.275 + 11 4.4532 4.6522 3.3149 2.8256 0.0459 0.7867 0.6090 0.0077 0.0000 -0.0158 -0.1376 0.276 + 12 5.1831 4.1429 3.0930 2.6153 0.0263 0.8188 0.6338 -0.0017 0.0000 -0.0182 -0.1444 0.279 + 13 6.0123 3.7903 3.4706 2.4170 0.0141 0.7850 0.6406 -0.0053 0.0000 -0.0176 -0.1591 0.277 + 14 6.9353 3.6075 3.3775 2.2635 0.0138 0.7722 0.6301 -0.0032 0.0000 -0.0178 -0.1570 0.278 + 15 7.8737 3.4215 3.2389 2.1280 0.0120 0.7654 0.6245 -0.0026 0.0000 -0.0178 -0.1557 0.278 + 16 8.8172 3.2345 3.0619 2.0025 0.0108 0.7619 0.6217 -0.0025 0.0000 -0.0176 -0.1549 0.278 + 17 9.7556 3.0486 2.8543 1.8825 0.0108 0.7599 0.6201 -0.0026 0.0000 -0.0174 -0.1544 0.278 + 18 10.6786 2.8657 2.6239 1.7671 0.0116 0.7588 0.6192 -0.0027 0.0000 -0.0172 -0.1540 0.278 + 19 11.5760 2.6879 2.3787 1.6548 0.0130 0.7577 0.6183 -0.0029 0.0000 -0.0169 -0.1535 0.277 + 20 12.4328 2.5181 2.1010 1.5454 0.0150 0.7553 0.6163 -0.0031 0.0000 -0.0165 -0.1527 0.277 + 21 13.2400 2.3582 1.8520 1.4378 0.0178 0.7504 0.6123 -0.0031 0.0000 -0.0158 -0.1512 0.276 + 22 13.9941 2.2087 1.6074 1.3299 0.0216 0.7410 0.6047 -0.0031 0.0000 -0.0147 -0.1486 0.274 + 23 14.6868 2.0715 1.3716 1.2186 0.0269 0.7240 0.5908 -0.0029 0.0000 -0.0131 -0.1440 0.272 + 24 15.3105 1.9479 1.1479 1.0997 0.0337 0.6947 0.5669 -0.0025 0.0000 -0.0106 -0.1364 0.269 + 25 15.8583 1.8393 0.9381 0.9669 0.0415 0.6468 0.5278 -0.0014 0.0000 -0.0079 -0.1253 0.265 + 26 16.3244 1.7470 0.7427 0.8147 0.0494 0.5734 0.4679 0.0021 0.0000 -0.0086 -0.1126 0.268 + 27 16.6722 1.4928 0.4131 0.6502 0.0579 1.4742 0.4382 -0.0115 0.0000 -0.0097 -0.0579 0.272 + 28 16.9098 1.1466 0.2292 0.4827 0.0704 1.4294 0.4249 -0.0263 0.0000 0.0073 -0.0483 0.233 + 29 17.0696 0.9138 0.1104 0.2989 0.0808 1.1158 0.3317 -0.0378 0.0000 0.0240 -0.0291 0.178 + 30 17.1499 0.7967 0.0322 0.1014 0.0867 0.4379 0.1302 -0.0278 0.0000 0.0163 -0.0081 0.125 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.29470 Clsurf = 0.05650 - CYsurf = 0.01758 Cmsurf = -0.26179 - CDsurf = 0.00799 Cnsurf = 0.00307 - CDisurf = 0.00799 CDvsurf = 0.00000 + CLsurf = 0.29524 Clsurf = 0.05655 + CYsurf = 0.01747 Cmsurf = -0.26208 + CDsurf = 0.00782 Cnsurf = 0.00308 + CDisurf = 0.00782 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.57624 CDsurf = 0.01559 + CLsurf = 0.57727 CDsurf = 0.01525 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 3.8928 0.1380 0.6071 0.4700 0.3889 0.0000 -0.0254 0.1237 0.304 - 32 -0.1025 7.6885 1.0492 3.6308 0.1375 0.6034 0.4671 0.0792 0.0000 -0.0256 0.1178 0.305 - 33 -0.2837 7.5620 1.7073 3.6065 0.1360 0.6117 0.4735 0.0596 0.0000 -0.0237 0.1172 0.300 - 34 -0.5530 7.3741 2.3052 3.5885 0.1332 0.6250 0.4839 0.0530 0.0000 -0.0209 0.1169 0.293 - 35 -0.9075 7.1267 2.8223 3.5569 0.1280 0.6418 0.4968 0.0477 0.0000 -0.0178 0.1170 0.286 - 36 -1.3432 6.8226 3.2414 3.5047 0.1183 0.6615 0.5121 0.0405 0.0000 -0.0151 0.1178 0.280 - 37 -1.8554 6.4651 3.5491 3.4258 0.1006 0.6829 0.5287 0.0367 0.0000 -0.0131 0.1195 0.275 - 38 -2.4386 6.0582 3.7368 3.3124 0.0825 0.7058 0.5464 0.0277 0.0000 -0.0122 0.1222 0.272 - 39 -3.0862 5.6062 3.8005 3.1628 0.0702 0.7291 0.5644 0.0213 0.0000 -0.0123 0.1259 0.272 - 40 -3.7613 5.1351 3.4440 2.9988 0.0588 0.7554 0.5847 0.0169 0.0000 -0.0135 0.1309 0.273 - 41 -4.4532 4.6522 3.3149 2.8163 0.0460 0.7842 0.6070 0.0074 0.0000 -0.0161 0.1374 0.277 - 42 -5.1831 4.1429 3.0930 2.6153 0.0269 0.8188 0.6338 -0.0016 0.0000 -0.0192 0.1452 0.280 - 43 -6.0123 3.7903 3.4706 2.4144 0.0145 0.7842 0.6399 -0.0053 0.0000 -0.0190 0.1602 0.280 - 44 -6.9353 3.6075 3.3775 2.2617 0.0141 0.7716 0.6296 -0.0032 0.0000 -0.0194 0.1582 0.281 - 45 -7.8737 3.4215 3.2389 2.1262 0.0121 0.7647 0.6240 -0.0026 0.0000 -0.0193 0.1570 0.281 - 46 -8.8172 3.2345 3.0619 2.0010 0.0109 0.7613 0.6212 -0.0025 0.0000 -0.0192 0.1562 0.281 - 47 -9.7556 3.0486 2.8543 1.8813 0.0109 0.7594 0.6197 -0.0026 0.0000 -0.0190 0.1557 0.281 - 48 -10.6786 2.8657 2.6240 1.7660 0.0117 0.7584 0.6188 -0.0026 0.0000 -0.0188 0.1553 0.280 - 49 -11.5760 2.6879 2.3787 1.6539 0.0131 0.7572 0.6179 -0.0028 0.0000 -0.0185 0.1548 0.280 - 50 -12.4328 2.5181 2.1010 1.5447 0.0151 0.7549 0.6160 -0.0030 0.0000 -0.0181 0.1540 0.279 - 51 -13.2400 2.3582 1.8520 1.4372 0.0178 0.7500 0.6120 -0.0031 0.0000 -0.0174 0.1526 0.278 - 52 -13.9941 2.2087 1.6074 1.3293 0.0216 0.7407 0.6044 -0.0031 0.0000 -0.0163 0.1499 0.277 - 53 -14.6868 2.0715 1.3716 1.2183 0.0269 0.7238 0.5906 -0.0029 0.0000 -0.0147 0.1453 0.275 - 54 -15.3105 1.9479 1.1479 1.0995 0.0337 0.6947 0.5668 -0.0025 0.0000 -0.0122 0.1378 0.272 - 55 -15.8583 1.8393 0.9381 0.9668 0.0416 0.6468 0.5278 -0.0014 0.0000 -0.0095 0.1267 0.268 - 56 -16.3244 1.7470 0.7427 0.8151 0.0496 0.5737 0.4682 0.0022 0.0000 -0.0102 0.1140 0.272 - 57 -16.6722 1.4928 0.4131 0.6506 0.0582 1.4751 0.4385 -0.0113 0.0000 -0.0110 0.0585 0.275 - 58 -16.9098 1.1466 0.2292 0.4829 0.0704 1.4298 0.4250 -0.0262 0.0000 0.0063 0.0487 0.235 - 59 -17.0696 0.9138 0.1104 0.2989 0.0807 1.1156 0.3316 -0.0376 0.0000 0.0234 0.0293 0.179 - 60 -17.1499 0.7967 0.0322 0.1013 0.0860 0.4376 0.1301 -0.0276 0.0000 0.0161 0.0082 0.126 + 31 -0.0114 7.7520 0.3539 3.9098 0.1379 0.6100 0.4722 0.3892 0.0000 -0.0269 0.1254 0.307 + 32 -0.1025 7.6885 1.0491 3.6461 0.1375 0.6060 0.4691 0.0791 0.0000 -0.0269 0.1192 0.307 + 33 -0.2837 7.5620 1.7073 3.6219 0.1363 0.6143 0.4756 0.0595 0.0000 -0.0250 0.1187 0.303 + 34 -0.5530 7.3741 2.3052 3.6028 0.1337 0.6277 0.4859 0.0514 0.0000 -0.0222 0.1184 0.296 + 35 -0.9075 7.1267 2.8223 3.5720 0.1286 0.6446 0.4990 0.0469 0.0000 -0.0191 0.1185 0.288 + 36 -1.3432 6.8226 3.2414 3.5192 0.1189 0.6642 0.5142 0.0408 0.0000 -0.0164 0.1193 0.282 + 37 -1.8554 6.4651 3.5491 3.4379 0.1013 0.6859 0.5310 0.0320 0.0000 -0.0144 0.1209 0.277 + 38 -2.4386 6.0582 3.7368 3.3248 0.0831 0.7084 0.5484 0.0282 0.0000 -0.0132 0.1235 0.274 + 39 -3.0862 5.6062 3.8005 3.1806 0.0711 0.7332 0.5676 0.0214 0.0000 -0.0131 0.1272 0.273 + 40 -3.7613 5.1351 3.4440 2.9929 0.0594 0.7540 0.5837 0.0161 0.0000 -0.0147 0.1317 0.275 + 41 -4.4532 4.6522 3.3149 2.8256 0.0459 0.7867 0.6090 0.0077 0.0000 -0.0158 0.1376 0.276 + 42 -5.1831 4.1429 3.0930 2.6153 0.0263 0.8188 0.6338 -0.0017 0.0000 -0.0182 0.1444 0.279 + 43 -6.0123 3.7903 3.4706 2.4170 0.0141 0.7850 0.6406 -0.0053 0.0000 -0.0176 0.1591 0.277 + 44 -6.9353 3.6075 3.3775 2.2635 0.0138 0.7722 0.6301 -0.0032 0.0000 -0.0178 0.1570 0.278 + 45 -7.8737 3.4215 3.2389 2.1280 0.0120 0.7654 0.6245 -0.0026 0.0000 -0.0178 0.1557 0.278 + 46 -8.8172 3.2345 3.0619 2.0025 0.0108 0.7619 0.6217 -0.0025 0.0000 -0.0176 0.1549 0.278 + 47 -9.7556 3.0486 2.8543 1.8825 0.0108 0.7599 0.6201 -0.0026 0.0000 -0.0174 0.1544 0.278 + 48 -10.6786 2.8657 2.6239 1.7671 0.0116 0.7588 0.6192 -0.0027 0.0000 -0.0172 0.1540 0.278 + 49 -11.5760 2.6879 2.3787 1.6548 0.0130 0.7577 0.6183 -0.0029 0.0000 -0.0169 0.1535 0.277 + 50 -12.4328 2.5181 2.1010 1.5454 0.0150 0.7553 0.6163 -0.0031 0.0000 -0.0165 0.1527 0.277 + 51 -13.2400 2.3582 1.8520 1.4378 0.0178 0.7504 0.6123 -0.0031 0.0000 -0.0158 0.1512 0.276 + 52 -13.9941 2.2087 1.6074 1.3299 0.0216 0.7410 0.6047 -0.0031 0.0000 -0.0147 0.1486 0.274 + 53 -14.6868 2.0715 1.3716 1.2186 0.0269 0.7240 0.5908 -0.0029 0.0000 -0.0131 0.1440 0.272 + 54 -15.3105 1.9479 1.1479 1.0997 0.0337 0.6947 0.5669 -0.0025 0.0000 -0.0106 0.1364 0.269 + 55 -15.8583 1.8393 0.9381 0.9669 0.0415 0.6468 0.5278 -0.0014 0.0000 -0.0079 0.1253 0.265 + 56 -16.3244 1.7470 0.7427 0.8147 0.0494 0.5734 0.4679 0.0021 0.0000 -0.0086 0.1126 0.268 + 57 -16.6722 1.4928 0.4131 0.6502 0.0579 1.4742 0.4382 -0.0115 0.0000 -0.0097 0.0579 0.272 + 58 -16.9098 1.1466 0.2292 0.4827 0.0704 1.4294 0.4249 -0.0263 0.0000 0.0073 0.0483 0.233 + 59 -17.0696 0.9138 0.1104 0.2989 0.0808 1.1158 0.3317 -0.0378 0.0000 0.0240 0.0291 0.178 + 60 -17.1499 0.7967 0.0322 0.1014 0.0867 0.4379 0.1302 -0.0278 0.0000 0.0163 0.0081 0.125 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02627 Clsurf = -0.00281 - CYsurf = -0.00416 Cmsurf = -0.12848 - CDsurf = 0.00150 Cnsurf = 0.00237 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02614 Clsurf = -0.00280 + CYsurf = -0.00414 Cmsurf = -0.12785 + CDsurf = 0.00150 Cnsurf = 0.00236 CDisurf = 0.00150 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16008 CDsurf = 0.00903 + CLsurf = 0.15927 CDsurf = 0.00900 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.5523 0.0898 0.1651 0.1265 0.0384 0.0000 -0.0074 -0.0341 0.308 - 62 0.0418 4.2566 0.2392 0.5097 0.0901 0.1557 0.1192 0.0111 0.0000 -0.0073 -0.0320 0.311 - 63 0.1156 4.2274 0.3930 0.5068 0.0900 0.1560 0.1195 0.0093 0.0000 -0.0069 -0.0317 0.308 - 64 0.2254 4.1839 0.5386 0.5061 0.0896 0.1575 0.1206 0.0090 0.0000 -0.0063 -0.0314 0.302 - 65 0.3698 4.1268 0.6730 0.5062 0.0887 0.1597 0.1223 0.0089 0.0000 -0.0055 -0.0311 0.295 - 66 0.5474 4.0565 0.7936 0.5061 0.0872 0.1625 0.1245 0.0088 0.0000 -0.0047 -0.0309 0.288 - 67 0.7617 3.9717 0.9441 0.5058 0.0849 0.1659 0.1271 0.0087 0.0000 -0.0040 -0.0309 0.281 - 68 1.0116 3.8728 1.0344 0.5055 0.0817 0.1701 0.1303 0.0087 0.0000 -0.0033 -0.0310 0.275 - 69 1.2891 3.7630 1.1046 0.5047 0.0778 0.1748 0.1339 0.0088 0.0000 -0.0027 -0.0313 0.270 - 70 1.5912 3.6435 1.1542 0.5041 0.0734 0.1803 0.1381 0.0089 0.0000 -0.0022 -0.0318 0.266 - 71 1.9146 3.5155 1.1831 0.5033 0.0690 0.1866 0.1429 0.0090 0.0000 -0.0018 -0.0325 0.263 - 72 2.2558 3.3805 1.1921 0.5024 0.0650 0.1937 0.1484 0.0091 0.0000 -0.0015 -0.0334 0.260 - 73 2.6109 3.2400 1.1821 0.5017 0.0617 0.2019 0.1546 0.0093 0.0000 -0.0011 -0.0344 0.257 - 74 2.9762 3.0955 1.1548 0.5006 0.0592 0.2108 0.1615 0.0094 0.0000 -0.0008 -0.0356 0.255 - 75 3.3476 2.9485 1.1122 0.4990 0.0573 0.2207 0.1690 0.0095 0.0000 -0.0005 -0.0370 0.253 - 76 3.7210 2.8008 1.0564 0.4963 0.0558 0.2311 0.1770 0.0097 0.0000 -0.0001 -0.0384 0.251 - 77 4.0924 2.6538 0.9900 0.4919 0.0549 0.2418 0.1852 0.0097 0.0000 0.0003 -0.0398 0.248 - 78 4.4577 2.5093 0.9155 0.4853 0.0543 0.2523 0.1933 0.0098 0.0000 0.0009 -0.0411 0.246 - 79 4.8128 2.3687 0.8353 0.4757 0.0542 0.2621 0.2007 0.0097 0.0000 0.0015 -0.0422 0.243 - 80 5.1540 2.2338 0.7518 0.4628 0.0546 0.2704 0.2071 0.0096 0.0000 0.0023 -0.0429 0.239 - 81 5.4774 2.1058 0.6671 0.4460 0.0555 0.2765 0.2118 0.0093 0.0000 0.0032 -0.0431 0.235 - 82 5.7795 1.9862 0.5830 0.4245 0.0568 0.2791 0.2138 0.0089 0.0000 0.0045 -0.0425 0.229 - 83 6.0570 1.8764 0.5012 0.3985 0.0585 0.2773 0.2124 0.0084 0.0000 0.0060 -0.0409 0.222 - 84 6.3069 1.7776 0.4225 0.3671 0.0606 0.2697 0.2066 0.0078 0.0000 0.0078 -0.0381 0.212 - 85 6.5264 1.6907 0.3478 0.3304 0.0627 0.2553 0.1956 0.0069 0.0000 0.0097 -0.0341 0.200 - 86 6.7314 1.6096 0.3326 0.2862 0.0649 0.2324 0.1780 0.0058 0.0000 0.0116 -0.0287 0.185 - 87 6.9144 1.5372 0.2507 0.2316 0.0671 0.1970 0.1509 0.0044 0.0000 0.0127 -0.0219 0.166 - 88 7.0535 1.4822 0.1746 0.1704 0.0688 0.1504 0.1152 0.0028 0.0000 0.0121 -0.0147 0.145 - 89 7.1471 1.4451 0.1029 0.1043 0.0700 0.0945 0.0724 0.0013 0.0000 0.0089 -0.0081 0.127 + 61 0.0047 4.2713 0.0803 0.5477 0.0899 0.1637 0.1254 0.0379 0.0000 -0.0073 -0.0338 0.309 + 62 0.0418 4.2566 0.2392 0.5057 0.0902 0.1544 0.1183 0.0110 0.0000 -0.0072 -0.0317 0.311 + 63 0.1156 4.2274 0.3930 0.5027 0.0901 0.1548 0.1186 0.0093 0.0000 -0.0069 -0.0315 0.308 + 64 0.2254 4.1839 0.5386 0.5021 0.0897 0.1563 0.1197 0.0089 0.0000 -0.0063 -0.0312 0.302 + 65 0.3698 4.1268 0.6730 0.5022 0.0888 0.1585 0.1214 0.0088 0.0000 -0.0055 -0.0309 0.295 + 66 0.5474 4.0565 0.7936 0.5021 0.0873 0.1612 0.1235 0.0087 0.0000 -0.0047 -0.0307 0.288 + 67 0.7617 3.9717 0.9441 0.5020 0.0849 0.1647 0.1261 0.0087 0.0000 -0.0040 -0.0306 0.281 + 68 1.0116 3.8728 1.0344 0.5015 0.0818 0.1687 0.1292 0.0087 0.0000 -0.0033 -0.0307 0.275 + 69 1.2891 3.7630 1.1046 0.5010 0.0779 0.1735 0.1329 0.0087 0.0000 -0.0027 -0.0310 0.270 + 70 1.5912 3.6435 1.1542 0.5004 0.0735 0.1790 0.1371 0.0088 0.0000 -0.0022 -0.0316 0.266 + 71 1.9146 3.5155 1.1831 0.4997 0.0691 0.1853 0.1419 0.0089 0.0000 -0.0018 -0.0323 0.263 + 72 2.2558 3.3805 1.1921 0.4991 0.0651 0.1924 0.1474 0.0091 0.0000 -0.0015 -0.0332 0.260 + 73 2.6109 3.2400 1.1821 0.4985 0.0619 0.2006 0.1536 0.0092 0.0000 -0.0012 -0.0342 0.258 + 74 2.9762 3.0955 1.1548 0.4978 0.0593 0.2097 0.1606 0.0094 0.0000 -0.0008 -0.0355 0.255 + 75 3.3476 2.9485 1.1122 0.4964 0.0574 0.2195 0.1682 0.0095 0.0000 -0.0005 -0.0368 0.253 + 76 3.7210 2.8008 1.0564 0.4939 0.0559 0.2300 0.1762 0.0097 0.0000 -0.0001 -0.0382 0.251 + 77 4.0924 2.6538 0.9900 0.4898 0.0550 0.2408 0.1844 0.0097 0.0000 0.0003 -0.0396 0.248 + 78 4.4577 2.5093 0.9155 0.4835 0.0544 0.2514 0.1926 0.0097 0.0000 0.0008 -0.0410 0.246 + 79 4.8128 2.3687 0.8353 0.4743 0.0543 0.2613 0.2001 0.0097 0.0000 0.0015 -0.0421 0.243 + 80 5.1540 2.2338 0.7518 0.4616 0.0547 0.2697 0.2066 0.0096 0.0000 0.0022 -0.0428 0.239 + 81 5.4774 2.1058 0.6671 0.4449 0.0555 0.2758 0.2113 0.0093 0.0000 0.0032 -0.0430 0.235 + 82 5.7795 1.9862 0.5830 0.4237 0.0568 0.2785 0.2133 0.0089 0.0000 0.0045 -0.0424 0.229 + 83 6.0570 1.8764 0.5012 0.3978 0.0586 0.2769 0.2121 0.0084 0.0000 0.0060 -0.0408 0.222 + 84 6.3069 1.7776 0.4225 0.3666 0.0606 0.2694 0.2063 0.0078 0.0000 0.0078 -0.0381 0.212 + 85 6.5264 1.6907 0.3478 0.3300 0.0627 0.2550 0.1954 0.0068 0.0000 0.0097 -0.0340 0.200 + 86 6.7314 1.6096 0.3326 0.2859 0.0649 0.2321 0.1778 0.0058 0.0000 0.0116 -0.0287 0.185 + 87 6.9144 1.5372 0.2507 0.2314 0.0671 0.1968 0.1507 0.0044 0.0000 0.0127 -0.0219 0.165 + 88 7.0535 1.4822 0.1746 0.1703 0.0688 0.1503 0.1151 0.0029 0.0000 0.0121 -0.0147 0.145 + 89 7.1471 1.4451 0.1029 0.1042 0.0700 0.0944 0.0723 0.0013 0.0000 0.0089 -0.0081 0.127 90 7.1941 1.4265 0.0340 0.0351 0.0706 0.0323 0.0247 -0.0002 0.0000 0.0033 -0.0026 0.116 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02627 Clsurf = 0.00281 - CYsurf = 0.00416 Cmsurf = -0.12848 - CDsurf = 0.00150 Cnsurf = -0.00237 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02614 Clsurf = 0.00280 + CYsurf = 0.00414 Cmsurf = -0.12785 + CDsurf = 0.00150 Cnsurf = -0.00236 CDisurf = 0.00150 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16007 CDsurf = 0.00903 + CLsurf = 0.15927 CDsurf = 0.00900 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.5523 0.0899 0.1651 0.1265 0.0384 0.0000 -0.0074 0.0341 0.308 - 92 -0.0418 4.2566 0.2392 0.5097 0.0901 0.1557 0.1192 0.0111 0.0000 -0.0073 0.0320 0.311 - 93 -0.1156 4.2274 0.3930 0.5068 0.0900 0.1560 0.1195 0.0093 0.0000 -0.0069 0.0317 0.308 - 94 -0.2254 4.1839 0.5386 0.5061 0.0896 0.1575 0.1206 0.0090 0.0000 -0.0063 0.0314 0.302 - 95 -0.3698 4.1268 0.6730 0.5062 0.0887 0.1597 0.1223 0.0089 0.0000 -0.0055 0.0311 0.295 - 96 -0.5474 4.0565 0.7936 0.5061 0.0872 0.1625 0.1245 0.0088 0.0000 -0.0047 0.0309 0.288 - 97 -0.7617 3.9717 0.9441 0.5058 0.0849 0.1659 0.1271 0.0087 0.0000 -0.0040 0.0309 0.281 - 98 -1.0116 3.8728 1.0344 0.5055 0.0817 0.1701 0.1303 0.0087 0.0000 -0.0033 0.0310 0.275 - 99 -1.2891 3.7630 1.1046 0.5047 0.0778 0.1748 0.1339 0.0088 0.0000 -0.0027 0.0313 0.270 - 100 -1.5912 3.6435 1.1542 0.5041 0.0734 0.1803 0.1381 0.0089 0.0000 -0.0022 0.0318 0.266 - 101 -1.9146 3.5155 1.1831 0.5033 0.0690 0.1866 0.1429 0.0090 0.0000 -0.0018 0.0325 0.263 - 102 -2.2558 3.3805 1.1921 0.5024 0.0650 0.1937 0.1484 0.0091 0.0000 -0.0015 0.0334 0.260 - 103 -2.6109 3.2400 1.1821 0.5017 0.0617 0.2019 0.1546 0.0093 0.0000 -0.0011 0.0344 0.257 - 104 -2.9762 3.0955 1.1548 0.5006 0.0592 0.2108 0.1615 0.0094 0.0000 -0.0008 0.0356 0.255 - 105 -3.3476 2.9485 1.1122 0.4989 0.0573 0.2207 0.1690 0.0095 0.0000 -0.0005 0.0370 0.253 - 106 -3.7210 2.8008 1.0564 0.4963 0.0558 0.2311 0.1770 0.0097 0.0000 -0.0001 0.0384 0.251 - 107 -4.0924 2.6538 0.9900 0.4919 0.0549 0.2418 0.1852 0.0097 0.0000 0.0003 0.0398 0.248 - 108 -4.4577 2.5093 0.9155 0.4853 0.0543 0.2523 0.1933 0.0098 0.0000 0.0009 0.0411 0.246 - 109 -4.8128 2.3687 0.8353 0.4757 0.0542 0.2621 0.2007 0.0097 0.0000 0.0015 0.0422 0.243 - 110 -5.1540 2.2338 0.7518 0.4628 0.0546 0.2704 0.2071 0.0096 0.0000 0.0023 0.0429 0.239 - 111 -5.4774 2.1058 0.6671 0.4460 0.0555 0.2765 0.2118 0.0093 0.0000 0.0032 0.0431 0.235 - 112 -5.7795 1.9862 0.5830 0.4245 0.0568 0.2791 0.2138 0.0089 0.0000 0.0045 0.0425 0.229 - 113 -6.0570 1.8764 0.5012 0.3985 0.0585 0.2773 0.2124 0.0084 0.0000 0.0060 0.0409 0.222 - 114 -6.3069 1.7776 0.4225 0.3671 0.0606 0.2697 0.2066 0.0078 0.0000 0.0078 0.0381 0.212 - 115 -6.5264 1.6907 0.3478 0.3304 0.0627 0.2553 0.1956 0.0069 0.0000 0.0097 0.0341 0.200 - 116 -6.7314 1.6096 0.3326 0.2862 0.0649 0.2324 0.1780 0.0058 0.0000 0.0116 0.0287 0.185 - 117 -6.9144 1.5372 0.2507 0.2316 0.0671 0.1970 0.1509 0.0044 0.0000 0.0127 0.0219 0.166 - 118 -7.0535 1.4822 0.1746 0.1704 0.0688 0.1504 0.1152 0.0028 0.0000 0.0121 0.0147 0.145 - 119 -7.1471 1.4451 0.1029 0.1043 0.0700 0.0945 0.0724 0.0013 0.0000 0.0089 0.0081 0.127 + 91 -0.0047 4.2713 0.0803 0.5477 0.0899 0.1637 0.1254 0.0379 0.0000 -0.0073 0.0338 0.309 + 92 -0.0418 4.2566 0.2392 0.5057 0.0902 0.1544 0.1183 0.0110 0.0000 -0.0072 0.0317 0.311 + 93 -0.1156 4.2274 0.3930 0.5027 0.0901 0.1548 0.1186 0.0093 0.0000 -0.0069 0.0315 0.308 + 94 -0.2254 4.1839 0.5386 0.5021 0.0897 0.1563 0.1197 0.0089 0.0000 -0.0063 0.0312 0.302 + 95 -0.3698 4.1268 0.6730 0.5022 0.0888 0.1585 0.1214 0.0088 0.0000 -0.0055 0.0309 0.295 + 96 -0.5474 4.0565 0.7936 0.5021 0.0873 0.1612 0.1235 0.0087 0.0000 -0.0047 0.0307 0.288 + 97 -0.7617 3.9717 0.9441 0.5020 0.0849 0.1647 0.1261 0.0087 0.0000 -0.0040 0.0306 0.281 + 98 -1.0116 3.8728 1.0344 0.5015 0.0818 0.1687 0.1292 0.0087 0.0000 -0.0033 0.0307 0.275 + 99 -1.2891 3.7630 1.1046 0.5010 0.0779 0.1735 0.1329 0.0087 0.0000 -0.0027 0.0310 0.270 + 100 -1.5912 3.6435 1.1542 0.5004 0.0735 0.1790 0.1371 0.0088 0.0000 -0.0022 0.0316 0.266 + 101 -1.9146 3.5155 1.1831 0.4997 0.0691 0.1853 0.1419 0.0089 0.0000 -0.0018 0.0323 0.263 + 102 -2.2558 3.3805 1.1921 0.4991 0.0651 0.1924 0.1474 0.0091 0.0000 -0.0015 0.0332 0.260 + 103 -2.6109 3.2400 1.1821 0.4985 0.0619 0.2006 0.1536 0.0092 0.0000 -0.0012 0.0342 0.258 + 104 -2.9762 3.0955 1.1548 0.4978 0.0593 0.2097 0.1606 0.0094 0.0000 -0.0008 0.0355 0.255 + 105 -3.3476 2.9485 1.1122 0.4964 0.0574 0.2195 0.1682 0.0095 0.0000 -0.0005 0.0368 0.253 + 106 -3.7210 2.8008 1.0564 0.4939 0.0559 0.2300 0.1762 0.0097 0.0000 -0.0001 0.0382 0.251 + 107 -4.0924 2.6538 0.9900 0.4898 0.0550 0.2408 0.1844 0.0097 0.0000 0.0003 0.0396 0.248 + 108 -4.4577 2.5093 0.9155 0.4835 0.0544 0.2514 0.1926 0.0097 0.0000 0.0008 0.0410 0.246 + 109 -4.8128 2.3687 0.8353 0.4743 0.0543 0.2613 0.2001 0.0097 0.0000 0.0015 0.0421 0.243 + 110 -5.1540 2.2338 0.7518 0.4616 0.0547 0.2697 0.2066 0.0096 0.0000 0.0022 0.0428 0.239 + 111 -5.4774 2.1058 0.6671 0.4449 0.0555 0.2758 0.2113 0.0093 0.0000 0.0032 0.0430 0.235 + 112 -5.7795 1.9862 0.5830 0.4237 0.0568 0.2785 0.2133 0.0089 0.0000 0.0045 0.0424 0.229 + 113 -6.0570 1.8764 0.5012 0.3978 0.0586 0.2769 0.2121 0.0084 0.0000 0.0060 0.0408 0.222 + 114 -6.3069 1.7776 0.4225 0.3666 0.0606 0.2694 0.2063 0.0078 0.0000 0.0078 0.0381 0.212 + 115 -6.5264 1.6907 0.3478 0.3300 0.0627 0.2550 0.1954 0.0068 0.0000 0.0097 0.0340 0.200 + 116 -6.7314 1.6096 0.3326 0.2859 0.0649 0.2321 0.1778 0.0058 0.0000 0.0116 0.0287 0.185 + 117 -6.9144 1.5372 0.2507 0.2314 0.0671 0.1968 0.1507 0.0044 0.0000 0.0127 0.0219 0.165 + 118 -7.0535 1.4822 0.1746 0.1703 0.0688 0.1503 0.1151 0.0029 0.0000 0.0121 0.0147 0.145 + 119 -7.1471 1.4451 0.1029 0.1042 0.0700 0.0944 0.0723 0.0013 0.0000 0.0089 0.0081 0.127 120 -7.1941 1.4265 0.0340 0.0351 0.0706 0.0323 0.0247 -0.0002 0.0000 0.0033 0.0026 0.116 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.336 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.342 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.350 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.358 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.368 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.368 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.359 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.355 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.334 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.304 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.272 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.267 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.256 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.253 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.250 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.245 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.189 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.171 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.151 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.130 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.331 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.351 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.351 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.368 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.367 + 126 0.0000 8.0598 2.2181 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.361 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.352 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.341 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.320 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.287 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.256 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.247 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.215 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.205 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.184 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.167 + 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.143 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.112 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00639 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.04689 + CLsurf = 0.00632 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = 0.04696 CDsurf = -0.00023 Cnsurf = -0.00000 CDisurf = -0.00023 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00644 CDsurf = -0.00023 + CLsurf = 0.00637 CDsurf = -0.00023 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.1404 0.1261 0.0633 0.0055 -0.0019 0.0000 0.0037 0.0003 -0.420 - 152 -1.3090 31.2096 11.6724 0.2039 0.1371 0.0253 0.0066 -0.0007 0.0000 0.0044 0.0007 -0.420 - 153 -0.9350 34.0626 12.7394 0.2270 0.1307 0.0162 0.0067 -0.0002 0.0000 0.0051 0.0012 -0.517 - 154 -0.5610 36.1619 13.5246 0.2404 0.1294 0.0111 0.0067 0.0002 0.0000 0.0055 0.0017 -0.573 - 155 -0.1870 37.5332 14.0374 0.2478 0.1304 0.0076 0.0066 0.0008 0.0000 0.0055 0.0027 -0.596 - 156 0.1870 37.5332 14.0374 0.2478 0.1304 0.0076 0.0066 0.0008 0.0000 0.0055 0.0027 -0.596 - 157 0.5610 36.1619 13.5246 0.2404 0.1294 0.0111 0.0067 0.0002 0.0000 0.0055 0.0017 -0.573 - 158 0.9350 34.0626 12.7394 0.2270 0.1307 0.0162 0.0067 -0.0002 0.0000 0.0051 0.0012 -0.517 - 159 1.3090 31.2096 11.6724 0.2039 0.1371 0.0253 0.0066 -0.0007 0.0000 0.0044 0.0007 -0.420 - 160 1.6830 26.5957 9.9468 0.1404 0.1261 0.0633 0.0055 -0.0019 0.0000 0.0037 0.0003 -0.420 + 151 -1.6830 26.5957 9.9468 0.1387 0.1260 0.0625 0.0054 -0.0019 0.0000 0.0037 0.0003 -0.433 + 152 -1.3090 31.2096 11.6724 0.2015 0.1371 0.0250 0.0065 -0.0007 0.0000 0.0045 0.0007 -0.432 + 153 -0.9350 34.0626 12.7394 0.2246 0.1309 0.0160 0.0066 -0.0002 0.0000 0.0052 0.0012 -0.529 + 154 -0.5610 36.1619 13.5246 0.2378 0.1296 0.0110 0.0066 0.0002 0.0000 0.0055 0.0017 -0.584 + 155 -0.1870 37.5332 14.0374 0.2453 0.1306 0.0075 0.0065 0.0008 0.0000 0.0056 0.0027 -0.607 + 156 0.1870 37.5332 14.0374 0.2453 0.1306 0.0075 0.0065 0.0008 0.0000 0.0056 0.0027 -0.607 + 157 0.5610 36.1619 13.5246 0.2378 0.1296 0.0110 0.0066 0.0002 0.0000 0.0055 0.0017 -0.584 + 158 0.9350 34.0626 12.7394 0.2246 0.1309 0.0160 0.0066 -0.0002 0.0000 0.0052 0.0012 -0.529 + 159 1.3090 31.2096 11.6724 0.2015 0.1371 0.0250 0.0065 -0.0007 0.0000 0.0045 0.0007 -0.432 + 160 1.6830 26.5957 9.9468 0.1387 0.1260 0.0625 0.0054 -0.0019 0.0000 0.0037 0.0003 -0.433 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = 0.00000 Clsurf = -0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = 0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 0.115 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.528 - 163 0.0000 34.0626 12.7394 -0.0000 0.0001 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.038 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.118 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.234 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.432 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.505 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.558 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.604 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.686 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 0.233 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.295 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.028 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.122 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.416 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.512 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.580 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.621 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.684 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_02_05.txt b/regression/scripts/AVL/avl_files/strip_forces_case_02_05.txt index 494743e021..3bcc1cef29 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_02_05.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_02_05.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.37543 Clsurf = -0.07294 - CYsurf = -0.02037 Cmsurf = -0.33630 - CDsurf = 0.01252 Cnsurf = -0.00691 - CDisurf = 0.01252 CDvsurf = 0.00000 + CLsurf = 0.37593 Clsurf = -0.07299 + CYsurf = -0.02019 Cmsurf = -0.33656 + CDsurf = 0.01224 Cnsurf = -0.00693 + CDisurf = 0.01224 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.73380 CDsurf = 0.02443 + CLsurf = 0.73476 CDsurf = 0.02389 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 4.8479 0.1735 0.7210 0.5584 0.5824 0.0000 -0.0313 -0.1541 0.306 - 2 0.1025 7.6885 1.0492 4.4533 0.1732 0.7349 0.5692 0.1166 0.0000 -0.0315 -0.1449 0.305 - 3 0.2837 7.5620 1.7073 4.4189 0.1718 0.7462 0.5780 0.0874 0.0000 -0.0292 -0.1441 0.301 - 4 0.5530 7.3741 2.3052 4.3979 0.1688 0.7634 0.5913 0.0779 0.0000 -0.0257 -0.1437 0.293 - 5 0.9075 7.1267 2.8223 4.3628 0.1629 0.7851 0.6081 0.0705 0.0000 -0.0218 -0.1439 0.286 - 6 1.3432 6.8226 3.2414 4.3058 0.1502 0.8114 0.6284 0.0603 0.0000 -0.0184 -0.1450 0.279 - 7 1.8554 6.4651 3.5491 4.2199 0.1247 0.8403 0.6508 0.0552 0.0000 -0.0158 -0.1473 0.274 - 8 2.4386 6.0582 3.7368 4.0949 0.0993 0.8725 0.6758 0.0424 0.0000 -0.0143 -0.1509 0.271 - 9 3.0862 5.6062 3.8005 3.9284 0.0857 0.9062 0.7019 0.0335 0.0000 -0.0141 -0.1558 0.270 - 10 3.7613 5.1351 3.4440 3.7487 0.0738 0.9453 0.7321 0.0278 0.0000 -0.0149 -0.1625 0.270 - 11 4.4532 4.6522 3.3149 3.5459 0.0597 0.9893 0.7662 0.0141 0.0000 -0.0173 -0.1711 0.273 - 12 5.1831 4.1429 3.0930 3.3200 0.0382 1.0423 0.8073 0.0010 0.0000 -0.0199 -0.1813 0.275 - 13 6.0123 3.7903 3.4706 3.0851 0.0237 1.0072 0.8206 -0.0046 0.0000 -0.0181 -0.2001 0.272 - 14 6.9353 3.6075 3.3775 2.9058 0.0220 0.9964 0.8118 -0.0021 0.0000 -0.0184 -0.1984 0.273 - 15 7.8737 3.4215 3.2389 2.7441 0.0185 0.9920 0.8083 -0.0017 0.0000 -0.0183 -0.1976 0.273 - 16 8.8172 3.2345 3.0619 2.5922 0.0162 0.9913 0.8077 -0.0020 0.0000 -0.0180 -0.1972 0.272 - 17 9.7556 3.0486 2.8543 2.4444 0.0158 0.9919 0.8081 -0.0024 0.0000 -0.0178 -0.1971 0.272 - 18 10.6786 2.8657 2.6240 2.3002 0.0167 0.9930 0.8090 -0.0029 0.0000 -0.0175 -0.1971 0.272 - 19 11.5760 2.6879 2.3787 2.1585 0.0185 0.9935 0.8095 -0.0034 0.0000 -0.0172 -0.1968 0.271 - 20 12.4328 2.5181 2.1010 2.0191 0.0210 0.9921 0.8083 -0.0039 0.0000 -0.0166 -0.1960 0.271 - 21 13.2400 2.3582 1.8520 1.8810 0.0246 0.9870 0.8042 -0.0042 0.0000 -0.0157 -0.1943 0.270 - 22 13.9941 2.2087 1.6074 1.7416 0.0296 0.9757 0.7949 -0.0044 0.0000 -0.0143 -0.1910 0.268 - 23 14.6868 2.0715 1.3716 1.5971 0.0366 0.9540 0.7773 -0.0042 0.0000 -0.0122 -0.1852 0.266 - 24 15.3105 1.9479 1.1479 1.4420 0.0455 0.9159 0.7463 -0.0036 0.0000 -0.0089 -0.1754 0.262 - 25 15.8583 1.8393 0.9381 1.2678 0.0556 0.8526 0.6947 -0.0018 0.0000 -0.0055 -0.1608 0.258 - 26 16.3244 1.7470 0.7427 1.0684 0.0660 0.7556 0.6156 0.0044 0.0000 -0.0069 -0.1445 0.261 - 27 16.6722 1.4928 0.4131 0.8519 0.0770 1.9292 0.5775 -0.0197 0.0000 -0.0090 -0.0754 0.266 - 28 16.9098 1.1466 0.2292 0.6315 0.0923 1.8730 0.5607 -0.0457 0.0000 0.0133 -0.0627 0.226 - 29 17.0696 0.9138 0.1104 0.3904 0.1048 1.4657 0.4387 -0.0658 0.0000 0.0348 -0.0375 0.171 - 30 17.1499 0.7967 0.0322 0.1322 0.1114 0.5793 0.1734 -0.0493 0.0000 0.0229 -0.0103 0.118 + 1 0.0114 7.7520 0.3539 4.8653 0.1735 0.7238 0.5606 0.5829 0.0000 -0.0328 -0.1558 0.308 + 2 0.1025 7.6885 1.0491 4.4685 0.1732 0.7375 0.5712 0.1166 0.0000 -0.0328 -0.1464 0.307 + 3 0.2837 7.5620 1.7073 4.4341 0.1721 0.7489 0.5800 0.0873 0.0000 -0.0305 -0.1456 0.303 + 4 0.5530 7.3741 2.3052 4.4114 0.1694 0.7662 0.5934 0.0754 0.0000 -0.0270 -0.1452 0.295 + 5 0.9075 7.1267 2.8223 4.3775 0.1635 0.7880 0.6103 0.0693 0.0000 -0.0232 -0.1454 0.288 + 6 1.3432 6.8226 3.2414 4.3198 0.1508 0.8140 0.6305 0.0606 0.0000 -0.0197 -0.1464 0.281 + 7 1.8554 6.4651 3.5491 4.2305 0.1253 0.8436 0.6534 0.0480 0.0000 -0.0170 -0.1486 0.276 + 8 2.4386 6.0582 3.7368 4.1063 0.0999 0.8749 0.6776 0.0431 0.0000 -0.0154 -0.1521 0.273 + 9 3.0862 5.6062 3.8005 3.9487 0.0865 0.9108 0.7055 0.0337 0.0000 -0.0148 -0.1571 0.271 + 10 3.7613 5.1351 3.4440 3.7345 0.0744 0.9419 0.7295 0.0264 0.0000 -0.0165 -0.1632 0.273 + 11 4.4532 4.6522 3.3149 3.5564 0.0597 0.9921 0.7684 0.0145 0.0000 -0.0170 -0.1713 0.272 + 12 5.1831 4.1429 3.0930 3.3177 0.0376 1.0416 0.8067 0.0009 0.0000 -0.0189 -0.1804 0.273 + 13 6.0123 3.7903 3.4706 3.0877 0.0233 1.0080 0.8213 -0.0045 0.0000 -0.0167 -0.1990 0.270 + 14 6.9353 3.6075 3.3775 2.9075 0.0218 0.9970 0.8123 -0.0021 0.0000 -0.0168 -0.1972 0.271 + 15 7.8737 3.4215 3.2389 2.7458 0.0183 0.9927 0.8088 -0.0017 0.0000 -0.0167 -0.1963 0.271 + 16 8.8172 3.2345 3.0619 2.5936 0.0161 0.9919 0.8081 -0.0020 0.0000 -0.0165 -0.1960 0.270 + 17 9.7556 3.0486 2.8543 2.4455 0.0157 0.9923 0.8085 -0.0025 0.0000 -0.0163 -0.1958 0.270 + 18 10.6786 2.8657 2.6239 2.3012 0.0167 0.9934 0.8094 -0.0029 0.0000 -0.0160 -0.1958 0.270 + 19 11.5760 2.6879 2.3787 2.1594 0.0184 0.9940 0.8098 -0.0035 0.0000 -0.0156 -0.1955 0.269 + 20 12.4328 2.5181 2.1010 2.0199 0.0210 0.9925 0.8087 -0.0040 0.0000 -0.0150 -0.1947 0.269 + 21 13.2400 2.3582 1.8520 1.8816 0.0246 0.9873 0.8044 -0.0043 0.0000 -0.0141 -0.1930 0.268 + 22 13.9941 2.2087 1.6074 1.7421 0.0296 0.9760 0.7952 -0.0044 0.0000 -0.0128 -0.1897 0.266 + 23 14.6868 2.0715 1.3716 1.5974 0.0365 0.9542 0.7775 -0.0042 0.0000 -0.0106 -0.1838 0.264 + 24 15.3105 1.9479 1.1479 1.4420 0.0454 0.9160 0.7463 -0.0036 0.0000 -0.0073 -0.1740 0.260 + 25 15.8583 1.8393 0.9381 1.2679 0.0555 0.8527 0.6947 -0.0019 0.0000 -0.0040 -0.1594 0.256 + 26 16.3244 1.7470 0.7427 1.0680 0.0657 0.7553 0.6154 0.0043 0.0000 -0.0054 -0.1431 0.259 + 27 16.6722 1.4928 0.4131 0.8515 0.0767 1.9283 0.5772 -0.0200 0.0000 -0.0077 -0.0747 0.263 + 28 16.9098 1.1466 0.2292 0.6314 0.0922 1.8727 0.5606 -0.0459 0.0000 0.0143 -0.0622 0.224 + 29 17.0696 0.9138 0.1104 0.3904 0.1050 1.4659 0.4388 -0.0661 0.0000 0.0354 -0.0372 0.169 + 30 17.1499 0.7967 0.0322 0.1323 0.1121 0.5797 0.1735 -0.0497 0.0000 0.0230 -0.0102 0.117 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.37542 Clsurf = 0.07294 - CYsurf = 0.02037 Cmsurf = -0.33630 - CDsurf = 0.01252 Cnsurf = 0.00691 - CDisurf = 0.01252 CDvsurf = 0.00000 + CLsurf = 0.37593 Clsurf = 0.07299 + CYsurf = 0.02019 Cmsurf = -0.33656 + CDsurf = 0.01224 Cnsurf = 0.00693 + CDisurf = 0.01224 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.73380 CDsurf = 0.02443 + CLsurf = 0.73476 CDsurf = 0.02389 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 4.8479 0.1736 0.7210 0.5584 0.5825 0.0000 -0.0313 0.1541 0.306 - 32 -0.1025 7.6885 1.0492 4.4533 0.1731 0.7349 0.5692 0.1166 0.0000 -0.0315 0.1449 0.305 - 33 -0.2837 7.5620 1.7073 4.4189 0.1718 0.7462 0.5780 0.0874 0.0000 -0.0292 0.1441 0.301 - 34 -0.5530 7.3741 2.3052 4.3979 0.1688 0.7634 0.5913 0.0779 0.0000 -0.0257 0.1437 0.293 - 35 -0.9075 7.1267 2.8223 4.3628 0.1629 0.7851 0.6081 0.0705 0.0000 -0.0218 0.1439 0.286 - 36 -1.3432 6.8226 3.2414 4.3058 0.1502 0.8114 0.6284 0.0603 0.0000 -0.0184 0.1450 0.279 - 37 -1.8554 6.4651 3.5491 4.2199 0.1247 0.8403 0.6508 0.0552 0.0000 -0.0158 0.1473 0.274 - 38 -2.4386 6.0582 3.7368 4.0949 0.0993 0.8725 0.6758 0.0424 0.0000 -0.0143 0.1509 0.271 - 39 -3.0862 5.6062 3.8005 3.9284 0.0857 0.9062 0.7019 0.0335 0.0000 -0.0141 0.1558 0.270 - 40 -3.7613 5.1351 3.4440 3.7487 0.0738 0.9452 0.7321 0.0278 0.0000 -0.0149 0.1625 0.270 - 41 -4.4532 4.6522 3.3149 3.5458 0.0597 0.9893 0.7662 0.0141 0.0000 -0.0173 0.1711 0.273 - 42 -5.1831 4.1429 3.0930 3.3199 0.0382 1.0423 0.8073 0.0010 0.0000 -0.0199 0.1813 0.275 - 43 -6.0123 3.7903 3.4706 3.0851 0.0237 1.0072 0.8206 -0.0046 0.0000 -0.0181 0.2001 0.272 - 44 -6.9353 3.6075 3.3775 2.9058 0.0220 0.9964 0.8118 -0.0021 0.0000 -0.0184 0.1984 0.273 - 45 -7.8737 3.4215 3.2389 2.7441 0.0185 0.9920 0.8082 -0.0017 0.0000 -0.0183 0.1976 0.273 - 46 -8.8172 3.2345 3.0619 2.5921 0.0162 0.9913 0.8077 -0.0020 0.0000 -0.0180 0.1972 0.272 - 47 -9.7556 3.0486 2.8543 2.4444 0.0158 0.9919 0.8081 -0.0024 0.0000 -0.0178 0.1971 0.272 - 48 -10.6786 2.8657 2.6240 2.3002 0.0167 0.9930 0.8090 -0.0029 0.0000 -0.0175 0.1971 0.272 - 49 -11.5760 2.6879 2.3787 2.1585 0.0185 0.9935 0.8095 -0.0034 0.0000 -0.0172 0.1968 0.271 - 50 -12.4328 2.5181 2.1010 2.0191 0.0210 0.9921 0.8083 -0.0039 0.0000 -0.0166 0.1960 0.271 - 51 -13.2400 2.3582 1.8520 1.8810 0.0246 0.9870 0.8042 -0.0042 0.0000 -0.0157 0.1943 0.270 - 52 -13.9941 2.2087 1.6074 1.7415 0.0296 0.9757 0.7949 -0.0044 0.0000 -0.0143 0.1910 0.268 - 53 -14.6868 2.0715 1.3716 1.5971 0.0366 0.9540 0.7773 -0.0042 0.0000 -0.0122 0.1852 0.266 - 54 -15.3105 1.9479 1.1479 1.4419 0.0455 0.9159 0.7462 -0.0036 0.0000 -0.0089 0.1754 0.262 - 55 -15.8583 1.8393 0.9381 1.2678 0.0556 0.8526 0.6947 -0.0018 0.0000 -0.0055 0.1608 0.258 - 56 -16.3244 1.7470 0.7427 1.0684 0.0660 0.7556 0.6156 0.0044 0.0000 -0.0069 0.1445 0.261 - 57 -16.6722 1.4928 0.4131 0.8519 0.0770 1.9292 0.5775 -0.0197 0.0000 -0.0090 0.0754 0.266 - 58 -16.9098 1.1466 0.2292 0.6315 0.0923 1.8730 0.5607 -0.0457 0.0000 0.0133 0.0627 0.226 - 59 -17.0696 0.9138 0.1104 0.3904 0.1048 1.4657 0.4387 -0.0658 0.0000 0.0348 0.0375 0.171 - 60 -17.1499 0.7967 0.0322 0.1322 0.1114 0.5793 0.1734 -0.0493 0.0000 0.0229 0.0103 0.118 + 31 -0.0114 7.7520 0.3539 4.8653 0.1735 0.7238 0.5606 0.5829 0.0000 -0.0328 0.1558 0.308 + 32 -0.1025 7.6885 1.0491 4.4685 0.1732 0.7375 0.5712 0.1166 0.0000 -0.0328 0.1464 0.307 + 33 -0.2837 7.5620 1.7073 4.4341 0.1721 0.7489 0.5800 0.0873 0.0000 -0.0305 0.1456 0.303 + 34 -0.5530 7.3741 2.3052 4.4114 0.1694 0.7662 0.5934 0.0754 0.0000 -0.0270 0.1452 0.295 + 35 -0.9075 7.1267 2.8223 4.3775 0.1635 0.7880 0.6103 0.0693 0.0000 -0.0232 0.1454 0.288 + 36 -1.3432 6.8226 3.2414 4.3198 0.1508 0.8140 0.6305 0.0606 0.0000 -0.0197 0.1464 0.281 + 37 -1.8554 6.4651 3.5491 4.2305 0.1253 0.8436 0.6534 0.0480 0.0000 -0.0170 0.1486 0.276 + 38 -2.4386 6.0582 3.7368 4.1063 0.0999 0.8749 0.6776 0.0431 0.0000 -0.0154 0.1521 0.273 + 39 -3.0862 5.6062 3.8005 3.9487 0.0865 0.9108 0.7055 0.0337 0.0000 -0.0148 0.1571 0.271 + 40 -3.7613 5.1351 3.4440 3.7345 0.0744 0.9419 0.7295 0.0264 0.0000 -0.0165 0.1632 0.273 + 41 -4.4532 4.6522 3.3149 3.5564 0.0597 0.9921 0.7684 0.0145 0.0000 -0.0170 0.1713 0.272 + 42 -5.1831 4.1429 3.0930 3.3177 0.0376 1.0416 0.8067 0.0009 0.0000 -0.0189 0.1804 0.273 + 43 -6.0123 3.7903 3.4706 3.0877 0.0233 1.0080 0.8213 -0.0045 0.0000 -0.0167 0.1990 0.270 + 44 -6.9353 3.6075 3.3775 2.9075 0.0218 0.9970 0.8123 -0.0021 0.0000 -0.0168 0.1972 0.271 + 45 -7.8737 3.4215 3.2389 2.7458 0.0183 0.9927 0.8088 -0.0017 0.0000 -0.0167 0.1963 0.271 + 46 -8.8172 3.2345 3.0619 2.5936 0.0161 0.9919 0.8081 -0.0020 0.0000 -0.0165 0.1960 0.270 + 47 -9.7556 3.0486 2.8543 2.4455 0.0157 0.9923 0.8085 -0.0025 0.0000 -0.0163 0.1958 0.270 + 48 -10.6786 2.8657 2.6239 2.3012 0.0167 0.9934 0.8094 -0.0029 0.0000 -0.0160 0.1958 0.270 + 49 -11.5760 2.6879 2.3787 2.1594 0.0184 0.9940 0.8098 -0.0035 0.0000 -0.0156 0.1955 0.269 + 50 -12.4328 2.5181 2.1010 2.0199 0.0210 0.9925 0.8087 -0.0040 0.0000 -0.0150 0.1947 0.269 + 51 -13.2400 2.3582 1.8520 1.8816 0.0246 0.9873 0.8044 -0.0043 0.0000 -0.0141 0.1930 0.268 + 52 -13.9941 2.2087 1.6074 1.7421 0.0296 0.9760 0.7952 -0.0044 0.0000 -0.0128 0.1897 0.266 + 53 -14.6868 2.0715 1.3716 1.5974 0.0365 0.9542 0.7774 -0.0042 0.0000 -0.0106 0.1838 0.264 + 54 -15.3105 1.9479 1.1479 1.4420 0.0454 0.9160 0.7463 -0.0036 0.0000 -0.0073 0.1740 0.260 + 55 -15.8583 1.8393 0.9381 1.2679 0.0555 0.8527 0.6947 -0.0019 0.0000 -0.0040 0.1594 0.256 + 56 -16.3244 1.7470 0.7427 1.0680 0.0657 0.7553 0.6154 0.0043 0.0000 -0.0054 0.1431 0.259 + 57 -16.6722 1.4928 0.4131 0.8515 0.0767 1.9283 0.5772 -0.0200 0.0000 -0.0077 0.0747 0.263 + 58 -16.9098 1.1466 0.2292 0.6314 0.0922 1.8727 0.5606 -0.0459 0.0000 0.0143 0.0622 0.224 + 59 -17.0696 0.9138 0.1104 0.3904 0.1050 1.4659 0.4388 -0.0661 0.0000 0.0354 0.0372 0.169 + 60 -17.1499 0.7967 0.0322 0.1323 0.1121 0.5797 0.1735 -0.0497 0.0000 0.0230 0.0102 0.117 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04162 Clsurf = -0.00435 - CYsurf = -0.00658 Cmsurf = -0.20366 - CDsurf = 0.00312 Cnsurf = 0.00363 - CDisurf = 0.00312 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04148 Clsurf = -0.00434 + CYsurf = -0.00656 Cmsurf = -0.20302 + CDsurf = 0.00311 Cnsurf = 0.00362 + CDisurf = 0.00311 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25359 CDsurf = 0.01879 + CLsurf = 0.25278 CDsurf = 0.01874 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.9668 0.1212 0.2823 0.2155 0.1022 0.0000 -0.0112 -0.0585 0.302 - 62 0.0418 4.2566 0.2392 0.8487 0.1217 0.2590 0.1977 0.0260 0.0000 -0.0111 -0.0528 0.306 - 63 0.1156 4.2274 0.3930 0.8405 0.1217 0.2590 0.1977 0.0211 0.0000 -0.0105 -0.0522 0.303 - 64 0.2254 4.1839 0.5386 0.8380 0.1213 0.2611 0.1993 0.0201 0.0000 -0.0095 -0.0516 0.298 - 65 0.3698 4.1268 0.6730 0.8377 0.1201 0.2648 0.2021 0.0196 0.0000 -0.0082 -0.0511 0.291 - 66 0.5474 4.0565 0.7936 0.8368 0.1181 0.2692 0.2055 0.0192 0.0000 -0.0069 -0.0508 0.283 - 67 0.7617 3.9717 0.9441 0.8352 0.1149 0.2745 0.2095 0.0191 0.0000 -0.0056 -0.0506 0.277 - 68 1.0116 3.8728 1.0344 0.8334 0.1104 0.2810 0.2145 0.0189 0.0000 -0.0044 -0.0507 0.271 - 69 1.2891 3.7630 1.1046 0.8301 0.1048 0.2882 0.2199 0.0189 0.0000 -0.0035 -0.0510 0.266 - 70 1.5912 3.6435 1.1542 0.8265 0.0985 0.2964 0.2262 0.0189 0.0000 -0.0026 -0.0517 0.262 - 71 1.9146 3.5155 1.1831 0.8220 0.0921 0.3056 0.2332 0.0190 0.0000 -0.0020 -0.0527 0.258 - 72 2.2558 3.3805 1.1921 0.8160 0.0865 0.3156 0.2408 0.0190 0.0000 -0.0014 -0.0539 0.256 - 73 2.6109 3.2400 1.1821 0.8099 0.0820 0.3269 0.2495 0.0192 0.0000 -0.0009 -0.0553 0.254 - 74 2.9762 3.0955 1.1548 0.8023 0.0786 0.3390 0.2587 0.0194 0.0000 -0.0004 -0.0569 0.252 - 75 3.3476 2.9485 1.1122 0.7934 0.0762 0.3521 0.2687 0.0194 0.0000 0.0001 -0.0587 0.250 - 76 3.7210 2.8008 1.0564 0.7827 0.0745 0.3658 0.2791 0.0195 0.0000 0.0006 -0.0605 0.248 - 77 4.0924 2.6538 0.9900 0.7691 0.0734 0.3794 0.2896 0.0195 0.0000 0.0012 -0.0622 0.246 - 78 4.4577 2.5093 0.9155 0.7526 0.0729 0.3928 0.2998 0.0195 0.0000 0.0019 -0.0638 0.244 - 79 4.8128 2.3687 0.8353 0.7318 0.0731 0.4047 0.3089 0.0191 0.0000 0.0028 -0.0651 0.241 - 80 5.1540 2.2338 0.7518 0.7067 0.0739 0.4146 0.3164 0.0188 0.0000 0.0039 -0.0658 0.238 - 81 5.4774 2.1058 0.6671 0.6767 0.0753 0.4213 0.3215 0.0182 0.0000 0.0053 -0.0657 0.233 - 82 5.7795 1.9862 0.5830 0.6404 0.0774 0.4228 0.3227 0.0173 0.0000 0.0071 -0.0644 0.228 - 83 6.0570 1.8764 0.5012 0.5982 0.0801 0.4182 0.3192 0.0162 0.0000 0.0093 -0.0618 0.221 - 84 6.3069 1.7776 0.4225 0.5487 0.0832 0.4050 0.3091 0.0149 0.0000 0.0119 -0.0574 0.212 - 85 6.5264 1.6907 0.3478 0.4922 0.0864 0.3822 0.2917 0.0131 0.0000 0.0147 -0.0513 0.200 - 86 6.7314 1.6096 0.3326 0.4252 0.0897 0.3470 0.2648 0.0110 0.0000 0.0174 -0.0432 0.184 - 87 6.9144 1.5372 0.2507 0.3433 0.0929 0.2935 0.2240 0.0082 0.0000 0.0190 -0.0329 0.165 - 88 7.0535 1.4822 0.1746 0.2521 0.0954 0.2237 0.1707 0.0052 0.0000 0.0180 -0.0221 0.145 - 89 7.1471 1.4451 0.1029 0.1542 0.0972 0.1405 0.1072 0.0023 0.0000 0.0132 -0.0123 0.127 + 61 0.0047 4.2713 0.0803 0.9617 0.1213 0.2809 0.2144 0.1014 0.0000 -0.0112 -0.0583 0.302 + 62 0.0418 4.2566 0.2392 0.8447 0.1217 0.2578 0.1967 0.0259 0.0000 -0.0111 -0.0526 0.306 + 63 0.1156 4.2274 0.3930 0.8362 0.1218 0.2577 0.1967 0.0211 0.0000 -0.0105 -0.0519 0.303 + 64 0.2254 4.1839 0.5386 0.8340 0.1214 0.2599 0.1984 0.0199 0.0000 -0.0095 -0.0514 0.298 + 65 0.3698 4.1268 0.6730 0.8336 0.1202 0.2635 0.2011 0.0194 0.0000 -0.0082 -0.0509 0.291 + 66 0.5474 4.0565 0.7936 0.8326 0.1181 0.2678 0.2044 0.0192 0.0000 -0.0069 -0.0505 0.284 + 67 0.7617 3.9717 0.9441 0.8315 0.1150 0.2733 0.2086 0.0190 0.0000 -0.0056 -0.0504 0.277 + 68 1.0116 3.8728 1.0344 0.8290 0.1105 0.2795 0.2133 0.0188 0.0000 -0.0044 -0.0504 0.271 + 69 1.2891 3.7630 1.1046 0.8265 0.1049 0.2869 0.2190 0.0187 0.0000 -0.0035 -0.0508 0.266 + 70 1.5912 3.6435 1.1542 0.8228 0.0986 0.2951 0.2252 0.0188 0.0000 -0.0027 -0.0515 0.262 + 71 1.9146 3.5155 1.1831 0.8182 0.0922 0.3042 0.2322 0.0189 0.0000 -0.0020 -0.0525 0.259 + 72 2.2558 3.3805 1.1921 0.8127 0.0866 0.3143 0.2398 0.0190 0.0000 -0.0014 -0.0537 0.256 + 73 2.6109 3.2400 1.1821 0.8067 0.0821 0.3256 0.2485 0.0192 0.0000 -0.0009 -0.0551 0.254 + 74 2.9762 3.0955 1.1548 0.7996 0.0787 0.3379 0.2579 0.0194 0.0000 -0.0004 -0.0568 0.252 + 75 3.3476 2.9485 1.1122 0.7909 0.0763 0.3509 0.2678 0.0194 0.0000 0.0001 -0.0585 0.250 + 76 3.7210 2.8008 1.0564 0.7801 0.0746 0.3645 0.2782 0.0195 0.0000 0.0006 -0.0603 0.248 + 77 4.0924 2.6538 0.9900 0.7670 0.0735 0.3784 0.2888 0.0195 0.0000 0.0012 -0.0621 0.246 + 78 4.4577 2.5093 0.9155 0.7508 0.0730 0.3918 0.2990 0.0193 0.0000 0.0019 -0.0637 0.244 + 79 4.8128 2.3687 0.8353 0.7304 0.0732 0.4040 0.3083 0.0191 0.0000 0.0028 -0.0650 0.241 + 80 5.1540 2.2338 0.7518 0.7056 0.0739 0.4140 0.3159 0.0187 0.0000 0.0039 -0.0657 0.238 + 81 5.4774 2.1058 0.6671 0.6756 0.0753 0.4206 0.3210 0.0182 0.0000 0.0053 -0.0656 0.233 + 82 5.7795 1.9862 0.5830 0.6394 0.0774 0.4222 0.3222 0.0172 0.0000 0.0071 -0.0644 0.228 + 83 6.0570 1.8764 0.5012 0.5975 0.0801 0.4177 0.3188 0.0162 0.0000 0.0093 -0.0617 0.221 + 84 6.3069 1.7776 0.4225 0.5483 0.0832 0.4048 0.3089 0.0149 0.0000 0.0119 -0.0574 0.211 + 85 6.5264 1.6907 0.3478 0.4919 0.0864 0.3820 0.2915 0.0130 0.0000 0.0147 -0.0512 0.200 + 86 6.7314 1.6096 0.3326 0.4249 0.0897 0.3467 0.2646 0.0110 0.0000 0.0173 -0.0431 0.184 + 87 6.9144 1.5372 0.2507 0.3430 0.0929 0.2932 0.2238 0.0082 0.0000 0.0190 -0.0329 0.165 + 88 7.0535 1.4822 0.1746 0.2520 0.0954 0.2236 0.1707 0.0052 0.0000 0.0180 -0.0221 0.145 + 89 7.1471 1.4451 0.1029 0.1541 0.0972 0.1404 0.1072 0.0023 0.0000 0.0132 -0.0123 0.127 90 7.1941 1.4265 0.0340 0.0519 0.0982 0.0481 0.0367 -0.0007 0.0000 0.0049 -0.0039 0.117 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04162 Clsurf = 0.00435 - CYsurf = 0.00658 Cmsurf = -0.20366 - CDsurf = 0.00312 Cnsurf = -0.00363 - CDisurf = 0.00312 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04148 Clsurf = 0.00434 + CYsurf = 0.00656 Cmsurf = -0.20302 + CDsurf = 0.00311 Cnsurf = -0.00362 + CDisurf = 0.00311 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25359 CDsurf = 0.01879 + CLsurf = 0.25278 CDsurf = 0.01874 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.9668 0.1213 0.2823 0.2155 0.1022 0.0000 -0.0112 0.0585 0.302 - 92 -0.0418 4.2566 0.2392 0.8487 0.1216 0.2590 0.1977 0.0260 0.0000 -0.0111 0.0528 0.306 - 93 -0.1156 4.2274 0.3930 0.8405 0.1217 0.2590 0.1977 0.0211 0.0000 -0.0105 0.0522 0.303 - 94 -0.2254 4.1839 0.5386 0.8380 0.1213 0.2611 0.1993 0.0201 0.0000 -0.0095 0.0516 0.298 - 95 -0.3698 4.1268 0.6730 0.8377 0.1201 0.2648 0.2021 0.0196 0.0000 -0.0082 0.0511 0.291 - 96 -0.5474 4.0565 0.7936 0.8368 0.1181 0.2692 0.2055 0.0192 0.0000 -0.0069 0.0508 0.283 - 97 -0.7617 3.9717 0.9441 0.8352 0.1149 0.2745 0.2095 0.0191 0.0000 -0.0056 0.0506 0.277 - 98 -1.0116 3.8728 1.0344 0.8334 0.1104 0.2810 0.2145 0.0189 0.0000 -0.0044 0.0507 0.271 - 99 -1.2891 3.7630 1.1046 0.8301 0.1048 0.2882 0.2199 0.0189 0.0000 -0.0035 0.0510 0.266 - 100 -1.5912 3.6435 1.1542 0.8265 0.0985 0.2964 0.2262 0.0189 0.0000 -0.0026 0.0517 0.262 - 101 -1.9146 3.5155 1.1831 0.8220 0.0921 0.3056 0.2332 0.0190 0.0000 -0.0020 0.0527 0.258 - 102 -2.2558 3.3805 1.1921 0.8160 0.0865 0.3156 0.2408 0.0190 0.0000 -0.0014 0.0539 0.256 - 103 -2.6109 3.2400 1.1821 0.8099 0.0820 0.3269 0.2495 0.0192 0.0000 -0.0009 0.0553 0.254 - 104 -2.9762 3.0955 1.1548 0.8023 0.0786 0.3390 0.2587 0.0194 0.0000 -0.0004 0.0569 0.252 - 105 -3.3476 2.9485 1.1122 0.7934 0.0762 0.3521 0.2687 0.0194 0.0000 0.0001 0.0587 0.250 - 106 -3.7210 2.8008 1.0564 0.7827 0.0745 0.3658 0.2791 0.0195 0.0000 0.0006 0.0605 0.248 - 107 -4.0924 2.6538 0.9900 0.7691 0.0734 0.3794 0.2896 0.0195 0.0000 0.0012 0.0622 0.246 - 108 -4.4577 2.5093 0.9155 0.7526 0.0729 0.3928 0.2998 0.0195 0.0000 0.0019 0.0638 0.244 - 109 -4.8128 2.3687 0.8353 0.7318 0.0731 0.4047 0.3089 0.0191 0.0000 0.0028 0.0651 0.241 - 110 -5.1540 2.2338 0.7518 0.7067 0.0739 0.4146 0.3164 0.0188 0.0000 0.0039 0.0658 0.238 - 111 -5.4774 2.1058 0.6671 0.6767 0.0753 0.4213 0.3215 0.0182 0.0000 0.0053 0.0657 0.233 - 112 -5.7795 1.9862 0.5830 0.6403 0.0774 0.4228 0.3227 0.0173 0.0000 0.0071 0.0644 0.228 - 113 -6.0570 1.8764 0.5012 0.5982 0.0801 0.4182 0.3192 0.0162 0.0000 0.0093 0.0618 0.221 - 114 -6.3069 1.7776 0.4225 0.5487 0.0832 0.4050 0.3091 0.0149 0.0000 0.0119 0.0574 0.212 - 115 -6.5264 1.6907 0.3478 0.4922 0.0864 0.3822 0.2917 0.0131 0.0000 0.0147 0.0513 0.200 - 116 -6.7314 1.6096 0.3326 0.4252 0.0897 0.3470 0.2648 0.0110 0.0000 0.0174 0.0432 0.184 - 117 -6.9144 1.5372 0.2507 0.3433 0.0929 0.2935 0.2240 0.0082 0.0000 0.0190 0.0329 0.165 - 118 -7.0535 1.4822 0.1746 0.2521 0.0954 0.2237 0.1707 0.0052 0.0000 0.0180 0.0221 0.145 - 119 -7.1471 1.4451 0.1029 0.1542 0.0972 0.1405 0.1072 0.0023 0.0000 0.0132 0.0123 0.127 + 91 -0.0047 4.2713 0.0803 0.9617 0.1213 0.2809 0.2144 0.1014 0.0000 -0.0112 0.0583 0.302 + 92 -0.0418 4.2566 0.2392 0.8447 0.1217 0.2578 0.1967 0.0259 0.0000 -0.0111 0.0526 0.306 + 93 -0.1156 4.2274 0.3930 0.8362 0.1218 0.2577 0.1967 0.0211 0.0000 -0.0105 0.0519 0.303 + 94 -0.2254 4.1839 0.5386 0.8340 0.1214 0.2599 0.1984 0.0199 0.0000 -0.0095 0.0514 0.298 + 95 -0.3698 4.1268 0.6730 0.8336 0.1202 0.2635 0.2011 0.0194 0.0000 -0.0082 0.0509 0.291 + 96 -0.5474 4.0565 0.7936 0.8326 0.1181 0.2678 0.2044 0.0192 0.0000 -0.0069 0.0505 0.284 + 97 -0.7617 3.9717 0.9441 0.8315 0.1150 0.2733 0.2086 0.0190 0.0000 -0.0056 0.0504 0.277 + 98 -1.0116 3.8728 1.0344 0.8290 0.1105 0.2795 0.2133 0.0188 0.0000 -0.0044 0.0504 0.271 + 99 -1.2891 3.7630 1.1046 0.8265 0.1049 0.2869 0.2190 0.0187 0.0000 -0.0035 0.0508 0.266 + 100 -1.5912 3.6435 1.1542 0.8228 0.0986 0.2951 0.2252 0.0188 0.0000 -0.0027 0.0515 0.262 + 101 -1.9146 3.5155 1.1831 0.8182 0.0922 0.3042 0.2322 0.0189 0.0000 -0.0020 0.0525 0.259 + 102 -2.2558 3.3805 1.1921 0.8127 0.0866 0.3143 0.2398 0.0190 0.0000 -0.0014 0.0537 0.256 + 103 -2.6109 3.2400 1.1821 0.8067 0.0821 0.3256 0.2485 0.0192 0.0000 -0.0009 0.0551 0.254 + 104 -2.9762 3.0955 1.1548 0.7996 0.0787 0.3379 0.2579 0.0194 0.0000 -0.0004 0.0568 0.252 + 105 -3.3476 2.9485 1.1122 0.7909 0.0763 0.3509 0.2678 0.0194 0.0000 0.0001 0.0585 0.250 + 106 -3.7210 2.8008 1.0564 0.7801 0.0746 0.3645 0.2782 0.0195 0.0000 0.0006 0.0603 0.248 + 107 -4.0924 2.6538 0.9900 0.7670 0.0735 0.3784 0.2888 0.0195 0.0000 0.0012 0.0621 0.246 + 108 -4.4577 2.5093 0.9155 0.7507 0.0730 0.3918 0.2990 0.0193 0.0000 0.0019 0.0637 0.244 + 109 -4.8128 2.3687 0.8353 0.7304 0.0732 0.4040 0.3083 0.0191 0.0000 0.0028 0.0650 0.241 + 110 -5.1540 2.2338 0.7518 0.7056 0.0739 0.4140 0.3159 0.0187 0.0000 0.0039 0.0657 0.238 + 111 -5.4774 2.1058 0.6671 0.6756 0.0753 0.4206 0.3210 0.0182 0.0000 0.0053 0.0656 0.233 + 112 -5.7795 1.9862 0.5830 0.6394 0.0774 0.4222 0.3222 0.0172 0.0000 0.0071 0.0644 0.228 + 113 -6.0570 1.8764 0.5012 0.5975 0.0801 0.4177 0.3188 0.0162 0.0000 0.0093 0.0617 0.221 + 114 -6.3069 1.7776 0.4225 0.5483 0.0832 0.4048 0.3089 0.0149 0.0000 0.0119 0.0574 0.211 + 115 -6.5264 1.6907 0.3478 0.4919 0.0864 0.3820 0.2915 0.0130 0.0000 0.0147 0.0512 0.200 + 116 -6.7314 1.6096 0.3326 0.4249 0.0897 0.3467 0.2646 0.0110 0.0000 0.0173 0.0431 0.184 + 117 -6.9144 1.5372 0.2507 0.3430 0.0929 0.2932 0.2238 0.0082 0.0000 0.0190 0.0329 0.165 + 118 -7.0535 1.4822 0.1746 0.2520 0.0954 0.2236 0.1707 0.0052 0.0000 0.0180 0.0221 0.145 + 119 -7.1471 1.4451 0.1029 0.1541 0.0972 0.1404 0.1072 0.0023 0.0000 0.0132 0.0123 0.127 120 -7.1941 1.4265 0.0340 0.0519 0.0982 0.0481 0.0367 -0.0007 0.0000 0.0049 0.0039 0.117 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.359 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.366 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.376 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.384 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.394 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.393 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.382 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.374 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.350 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.316 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.281 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.273 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.262 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.258 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.250 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.212 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.200 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.184 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.167 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.146 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.126 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.109 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.351 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.370 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.371 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.389 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.388 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.381 + 127 0.0000 7.4000 2.2957 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.371 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.357 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.333 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.297 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.263 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.258 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.250 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.242 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.201 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.180 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.162 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.139 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.115 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.107 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01089 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.06665 - CDsurf = -0.00024 Cnsurf = -0.00000 - CDisurf = -0.00024 CDvsurf = 0.00000 + CLsurf = 0.01082 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.06672 + CDsurf = -0.00025 Cnsurf = 0.00000 + CDisurf = -0.00025 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01098 CDsurf = -0.00025 + CLsurf = 0.01091 CDsurf = -0.00025 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.2475 0.1789 0.1049 0.0098 -0.0031 0.0000 0.0048 0.0003 -0.238 - 152 -1.3090 31.2096 11.6724 0.3502 0.1918 0.0427 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.268 - 153 -0.9350 34.0626 12.7394 0.3843 0.1773 0.0273 0.0114 -0.0002 0.0000 0.0071 0.0014 -0.370 - 154 -0.5610 36.1619 13.5246 0.4030 0.1723 0.0186 0.0112 0.0005 0.0000 0.0076 0.0022 -0.431 - 155 -0.1870 37.5332 14.0374 0.4135 0.1724 0.0126 0.0109 0.0016 0.0000 0.0077 0.0034 -0.460 - 156 0.1870 37.5332 14.0374 0.4135 0.1724 0.0126 0.0109 0.0016 0.0000 0.0077 0.0034 -0.460 - 157 0.5610 36.1619 13.5246 0.4030 0.1723 0.0186 0.0112 0.0005 0.0000 0.0076 0.0022 -0.431 - 158 0.9350 34.0626 12.7394 0.3843 0.1773 0.0273 0.0114 -0.0002 0.0000 0.0071 0.0014 -0.370 - 159 1.3090 31.2096 11.6724 0.3502 0.1918 0.0427 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.268 - 160 1.6830 26.5957 9.9468 0.2475 0.1789 0.1049 0.0098 -0.0031 0.0000 0.0048 0.0003 -0.238 + 151 -1.6830 26.5957 9.9468 0.2458 0.1788 0.1042 0.0097 -0.0031 0.0000 0.0048 0.0003 -0.243 + 152 -1.3090 31.2096 11.6724 0.3479 0.1918 0.0425 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.273 + 153 -0.9350 34.0626 12.7394 0.3818 0.1775 0.0271 0.0113 -0.0002 0.0000 0.0071 0.0014 -0.376 + 154 -0.5610 36.1619 13.5246 0.4005 0.1726 0.0185 0.0111 0.0005 0.0000 0.0076 0.0022 -0.437 + 155 -0.1870 37.5332 14.0374 0.4110 0.1726 0.0126 0.0108 0.0016 0.0000 0.0078 0.0035 -0.466 + 156 0.1870 37.5332 14.0374 0.4110 0.1726 0.0126 0.0108 0.0016 0.0000 0.0078 0.0035 -0.466 + 157 0.5610 36.1619 13.5246 0.4005 0.1725 0.0185 0.0111 0.0005 0.0000 0.0076 0.0022 -0.437 + 158 0.9350 34.0626 12.7394 0.3818 0.1775 0.0271 0.0113 -0.0002 0.0000 0.0071 0.0014 -0.376 + 159 1.3090 31.2096 11.6724 0.3479 0.1918 0.0425 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.273 + 160 1.6830 26.5957 9.9468 0.2458 0.1788 0.1042 0.0097 -0.0031 0.0000 0.0048 0.0003 -0.243 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00000 Clsurf = -0.00000 + CLsurf = -0.00000 Clsurf = -0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = 0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0002 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.617 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.192 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.055 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.398 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.505 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.578 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.639 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.730 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.383 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.137 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.080 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.401 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.523 + 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.606 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.657 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.729 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_02_06.txt b/regression/scripts/AVL/avl_files/strip_forces_case_02_06.txt index 9e13ec0f87..3ad1aae1ac 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_02_06.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_02_06.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.49489 Clsurf = -0.09692 - CYsurf = -0.02261 Cmsurf = -0.44551 - CDsurf = 0.02115 Cnsurf = -0.01514 - CDisurf = 0.02115 CDvsurf = 0.00000 + CLsurf = 0.49535 Clsurf = -0.09696 + CYsurf = -0.02229 Cmsurf = -0.44572 + CDsurf = 0.02067 Cnsurf = -0.01518 + CDisurf = 0.02067 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.96674 CDsurf = 0.04129 + CLsurf = 0.96759 CDsurf = 0.04035 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 6.3025 0.2264 0.8494 0.6592 0.9400 0.0000 -0.0398 -0.2002 0.310 - 2 0.1025 7.6885 1.0492 5.6602 0.2263 0.9210 0.7148 0.1852 0.0000 -0.0402 -0.1850 0.306 - 3 0.2837 7.5620 1.7073 5.6070 0.2250 0.9386 0.7285 0.1380 0.0000 -0.0373 -0.1837 0.301 - 4 0.5530 7.3741 2.3052 5.5809 0.2219 0.9621 0.7467 0.1233 0.0000 -0.0327 -0.1832 0.294 - 5 0.9075 7.1267 2.8223 5.5403 0.2148 0.9916 0.7696 0.1121 0.0000 -0.0277 -0.1834 0.286 - 6 1.3432 6.8226 3.2414 5.4762 0.1976 1.0282 0.7980 0.0964 0.0000 -0.0232 -0.1850 0.279 - 7 1.8554 6.4651 3.5491 5.3801 0.1606 1.0684 0.8292 0.0892 0.0000 -0.0195 -0.1881 0.274 - 8 2.4386 6.0582 3.7368 5.2379 0.1243 1.1153 0.8656 0.0698 0.0000 -0.0174 -0.1931 0.270 - 9 3.0862 5.6062 3.8005 5.0461 0.1086 1.1647 0.9040 0.0566 0.0000 -0.0167 -0.1999 0.268 - 10 3.7613 5.1351 3.4440 4.8449 0.0962 1.2233 0.9494 0.0490 0.0000 -0.0169 -0.2091 0.268 - 11 4.4532 4.6522 3.3149 4.6137 0.0803 1.2913 1.0021 0.0278 0.0000 -0.0191 -0.2208 0.269 - 12 5.1831 4.1429 3.0930 4.3523 0.0551 1.3728 1.0654 0.0077 0.0000 -0.0209 -0.2344 0.270 - 13 6.0123 3.7903 3.4706 4.0647 0.0375 1.3387 1.0893 -0.0017 0.0000 -0.0160 -0.2586 0.265 - 14 6.9353 3.6075 3.3775 3.8461 0.0338 1.3303 1.0824 0.0013 0.0000 -0.0162 -0.2573 0.265 - 15 7.8737 3.4215 3.2389 3.6459 0.0279 1.3296 1.0819 0.0011 0.0000 -0.0160 -0.2570 0.265 - 16 8.8172 3.2345 3.0619 3.4551 0.0241 1.3331 1.0847 -0.0001 0.0000 -0.0157 -0.2573 0.264 - 17 9.7556 3.0486 2.8543 3.2662 0.0232 1.3374 1.0882 -0.0014 0.0000 -0.0154 -0.2578 0.264 - 18 10.6786 2.8657 2.6240 3.0798 0.0242 1.3418 1.0918 -0.0026 0.0000 -0.0150 -0.2582 0.264 - 19 11.5760 2.6879 2.3787 2.8948 0.0265 1.3449 1.0944 -0.0039 0.0000 -0.0145 -0.2583 0.263 - 20 12.4328 2.5181 2.1010 2.7116 0.0299 1.3450 1.0944 -0.0051 0.0000 -0.0137 -0.2576 0.263 - 21 13.2400 2.3582 1.8520 2.5287 0.0347 1.3396 1.0900 -0.0059 0.0000 -0.0126 -0.2556 0.262 - 22 13.9941 2.2087 1.6074 2.3432 0.0415 1.3254 1.0784 -0.0064 0.0000 -0.0107 -0.2513 0.260 - 23 14.6868 2.0715 1.3716 2.1500 0.0509 1.2966 1.0551 -0.0063 0.0000 -0.0078 -0.2435 0.257 - 24 15.3105 1.9479 1.1479 1.9417 0.0629 1.2452 1.0132 -0.0054 0.0000 -0.0035 -0.2303 0.253 - 25 15.8583 1.8393 0.9381 1.7070 0.0765 1.1587 0.9429 -0.0024 0.0000 0.0009 -0.2108 0.249 - 26 16.3244 1.7470 0.7427 1.4380 0.0903 1.0253 0.8343 0.0090 0.0000 -0.0017 -0.1891 0.252 - 27 16.6722 1.4928 0.4131 1.1455 0.1049 2.5717 0.7859 -0.0363 0.0000 -0.0054 -0.1009 0.257 - 28 16.9098 1.1466 0.2292 0.8483 0.1248 2.5085 0.7667 -0.0841 0.0000 0.0244 -0.0840 0.218 - 29 17.0696 0.9138 0.1104 0.5239 0.1408 1.9774 0.6043 -0.1214 0.0000 0.0520 -0.0501 0.164 - 30 17.1499 0.7967 0.0322 0.1774 0.1492 0.7948 0.2429 -0.0927 0.0000 0.0330 -0.0137 0.114 + 1 0.0114 7.7520 0.3539 6.3202 0.2265 0.8523 0.6614 0.9407 0.0000 -0.0413 -0.2020 0.312 + 2 0.1025 7.6885 1.0491 5.6753 0.2264 0.9236 0.7168 0.1851 0.0000 -0.0415 -0.1864 0.308 + 3 0.2837 7.5620 1.7073 5.6220 0.2254 0.9412 0.7305 0.1380 0.0000 -0.0385 -0.1851 0.303 + 4 0.5530 7.3741 2.3052 5.5929 0.2224 0.9651 0.7491 0.1193 0.0000 -0.0340 -0.1846 0.295 + 5 0.9075 7.1267 2.8223 5.5543 0.2154 0.9946 0.7719 0.1100 0.0000 -0.0290 -0.1849 0.288 + 6 1.3432 6.8226 3.2414 5.4891 0.1982 1.0305 0.7998 0.0969 0.0000 -0.0245 -0.1864 0.281 + 7 1.8554 6.4651 3.5491 5.3878 0.1612 1.0727 0.8325 0.0775 0.0000 -0.0209 -0.1895 0.275 + 8 2.4386 6.0582 3.7368 5.2475 0.1249 1.1171 0.8670 0.0707 0.0000 -0.0185 -0.1943 0.271 + 9 3.0862 5.6062 3.8005 5.0709 0.1095 1.1705 0.9084 0.0569 0.0000 -0.0173 -0.2013 0.269 + 10 3.7613 5.1351 3.4440 4.8152 0.0968 1.2164 0.9440 0.0461 0.0000 -0.0192 -0.2097 0.270 + 11 4.4532 4.6522 3.3149 4.6264 0.0802 1.2947 1.0048 0.0286 0.0000 -0.0187 -0.2210 0.269 + 12 5.1831 4.1429 3.0930 4.3460 0.0545 1.3709 1.0639 0.0073 0.0000 -0.0199 -0.2333 0.269 + 13 6.0123 3.7903 3.4706 4.0673 0.0370 1.3395 1.0900 -0.0016 0.0000 -0.0146 -0.2575 0.263 + 14 6.9353 3.6075 3.3775 3.8474 0.0336 1.3307 1.0828 0.0013 0.0000 -0.0147 -0.2561 0.264 + 15 7.8737 3.4215 3.2389 3.6476 0.0278 1.3302 1.0824 0.0011 0.0000 -0.0145 -0.2558 0.263 + 16 8.8172 3.2345 3.0619 3.4565 0.0240 1.3337 1.0852 -0.0001 0.0000 -0.0142 -0.2561 0.263 + 17 9.7556 3.0486 2.8543 3.2671 0.0231 1.3378 1.0885 -0.0015 0.0000 -0.0139 -0.2565 0.263 + 18 10.6786 2.8657 2.6239 3.0808 0.0242 1.3422 1.0921 -0.0027 0.0000 -0.0135 -0.2570 0.262 + 19 11.5760 2.6879 2.3787 2.8957 0.0265 1.3453 1.0947 -0.0040 0.0000 -0.0130 -0.2570 0.262 + 20 12.4328 2.5181 2.1010 2.7124 0.0299 1.3454 1.0947 -0.0052 0.0000 -0.0122 -0.2563 0.261 + 21 13.2400 2.3582 1.8520 2.5294 0.0347 1.3399 1.0903 -0.0060 0.0000 -0.0110 -0.2542 0.260 + 22 13.9941 2.2087 1.6074 2.3438 0.0415 1.3257 1.0787 -0.0065 0.0000 -0.0092 -0.2500 0.258 + 23 14.6868 2.0715 1.3716 2.1502 0.0509 1.2968 1.0552 -0.0064 0.0000 -0.0062 -0.2422 0.256 + 24 15.3105 1.9479 1.1479 1.9417 0.0629 1.2452 1.0132 -0.0055 0.0000 -0.0019 -0.2290 0.252 + 25 15.8583 1.8393 0.9381 1.7073 0.0765 1.1589 0.9430 -0.0026 0.0000 0.0024 -0.2095 0.247 + 26 16.3244 1.7470 0.7427 1.4376 0.0901 1.0250 0.8340 0.0089 0.0000 -0.0001 -0.1877 0.250 + 27 16.6722 1.4928 0.4131 1.1450 0.1046 2.5707 0.7857 -0.0366 0.0000 -0.0041 -0.1003 0.255 + 28 16.9098 1.1466 0.2292 0.8482 0.1247 2.5083 0.7666 -0.0844 0.0000 0.0253 -0.0835 0.217 + 29 17.0696 0.9138 0.1104 0.5239 0.1410 1.9777 0.6044 -0.1218 0.0000 0.0526 -0.0499 0.163 + 30 17.1499 0.7967 0.0322 0.1774 0.1499 0.7954 0.2431 -0.0932 0.0000 0.0332 -0.0136 0.114 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.49489 Clsurf = 0.09692 - CYsurf = 0.02261 Cmsurf = -0.44551 - CDsurf = 0.02115 Cnsurf = 0.01514 - CDisurf = 0.02115 CDvsurf = 0.00000 + CLsurf = 0.49535 Clsurf = 0.09696 + CYsurf = 0.02229 Cmsurf = -0.44572 + CDsurf = 0.02067 Cnsurf = 0.01518 + CDisurf = 0.02067 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.96674 CDsurf = 0.04129 + CLsurf = 0.96759 CDsurf = 0.04035 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 6.3025 0.2267 0.8494 0.6592 0.9401 0.0000 -0.0398 0.2002 0.310 - 32 -0.1025 7.6885 1.0492 5.6602 0.2263 0.9210 0.7148 0.1852 0.0000 -0.0402 0.1850 0.306 - 33 -0.2837 7.5620 1.7073 5.6070 0.2250 0.9386 0.7285 0.1380 0.0000 -0.0373 0.1837 0.301 - 34 -0.5530 7.3741 2.3052 5.5809 0.2219 0.9621 0.7467 0.1233 0.0000 -0.0327 0.1832 0.294 - 35 -0.9075 7.1267 2.8223 5.5403 0.2148 0.9916 0.7696 0.1121 0.0000 -0.0277 0.1834 0.286 - 36 -1.3432 6.8226 3.2414 5.4761 0.1976 1.0282 0.7980 0.0964 0.0000 -0.0232 0.1850 0.279 - 37 -1.8554 6.4651 3.5491 5.3801 0.1606 1.0684 0.8292 0.0892 0.0000 -0.0195 0.1881 0.274 - 38 -2.4386 6.0582 3.7368 5.2379 0.1243 1.1153 0.8656 0.0698 0.0000 -0.0174 0.1931 0.270 - 39 -3.0862 5.6062 3.8005 5.0461 0.1086 1.1647 0.9040 0.0566 0.0000 -0.0167 0.1999 0.268 - 40 -3.7613 5.1351 3.4440 4.8449 0.0962 1.2233 0.9494 0.0490 0.0000 -0.0169 0.2091 0.268 - 41 -4.4532 4.6522 3.3149 4.6137 0.0803 1.2913 1.0021 0.0278 0.0000 -0.0191 0.2208 0.269 - 42 -5.1831 4.1429 3.0930 4.3523 0.0551 1.3728 1.0654 0.0077 0.0000 -0.0209 0.2344 0.270 - 43 -6.0123 3.7903 3.4706 4.0646 0.0375 1.3387 1.0893 -0.0017 0.0000 -0.0160 0.2586 0.265 - 44 -6.9353 3.6075 3.3775 3.8461 0.0338 1.3303 1.0824 0.0013 0.0000 -0.0162 0.2573 0.265 - 45 -7.8737 3.4215 3.2389 3.6459 0.0279 1.3296 1.0819 0.0011 0.0000 -0.0160 0.2570 0.265 - 46 -8.8172 3.2345 3.0619 3.4551 0.0241 1.3331 1.0847 -0.0001 0.0000 -0.0157 0.2573 0.264 - 47 -9.7556 3.0486 2.8543 3.2662 0.0232 1.3374 1.0882 -0.0014 0.0000 -0.0154 0.2578 0.264 - 48 -10.6786 2.8657 2.6240 3.0798 0.0242 1.3418 1.0918 -0.0026 0.0000 -0.0150 0.2582 0.264 - 49 -11.5760 2.6879 2.3787 2.8948 0.0265 1.3449 1.0943 -0.0039 0.0000 -0.0145 0.2583 0.263 - 50 -12.4328 2.5181 2.1010 2.7116 0.0299 1.3450 1.0944 -0.0051 0.0000 -0.0137 0.2576 0.263 - 51 -13.2400 2.3582 1.8520 2.5287 0.0347 1.3395 1.0900 -0.0059 0.0000 -0.0126 0.2556 0.262 - 52 -13.9941 2.2087 1.6074 2.3432 0.0415 1.3253 1.0784 -0.0064 0.0000 -0.0107 0.2513 0.260 - 53 -14.6868 2.0715 1.3716 2.1499 0.0509 1.2966 1.0550 -0.0063 0.0000 -0.0078 0.2435 0.257 - 54 -15.3105 1.9479 1.1479 1.9417 0.0629 1.2452 1.0132 -0.0054 0.0000 -0.0035 0.2303 0.253 - 55 -15.8583 1.8393 0.9381 1.7070 0.0765 1.1587 0.9428 -0.0024 0.0000 0.0009 0.2108 0.249 - 56 -16.3244 1.7470 0.7427 1.4380 0.0903 1.0253 0.8343 0.0090 0.0000 -0.0017 0.1891 0.252 - 57 -16.6722 1.4928 0.4131 1.1454 0.1049 2.5716 0.7859 -0.0363 0.0000 -0.0054 0.1009 0.257 - 58 -16.9098 1.1466 0.2292 0.8483 0.1248 2.5085 0.7666 -0.0841 0.0000 0.0244 0.0840 0.218 - 59 -17.0696 0.9138 0.1104 0.5239 0.1408 1.9774 0.6043 -0.1214 0.0000 0.0520 0.0501 0.164 - 60 -17.1499 0.7967 0.0322 0.1774 0.1492 0.7948 0.2429 -0.0927 0.0000 0.0330 0.0137 0.114 + 31 -0.0114 7.7520 0.3539 6.3202 0.2266 0.8523 0.6614 0.9407 0.0000 -0.0413 0.2020 0.312 + 32 -0.1025 7.6885 1.0491 5.6753 0.2264 0.9236 0.7168 0.1851 0.0000 -0.0415 0.1864 0.308 + 33 -0.2837 7.5620 1.7073 5.6220 0.2253 0.9412 0.7305 0.1380 0.0000 -0.0385 0.1851 0.303 + 34 -0.5530 7.3741 2.3052 5.5929 0.2224 0.9651 0.7491 0.1193 0.0000 -0.0340 0.1846 0.295 + 35 -0.9075 7.1267 2.8223 5.5543 0.2154 0.9946 0.7719 0.1100 0.0000 -0.0290 0.1849 0.288 + 36 -1.3432 6.8226 3.2414 5.4891 0.1982 1.0305 0.7998 0.0969 0.0000 -0.0245 0.1864 0.281 + 37 -1.8554 6.4651 3.5491 5.3878 0.1612 1.0727 0.8325 0.0775 0.0000 -0.0209 0.1895 0.275 + 38 -2.4386 6.0582 3.7368 5.2475 0.1249 1.1171 0.8670 0.0707 0.0000 -0.0185 0.1943 0.271 + 39 -3.0862 5.6062 3.8005 5.0709 0.1095 1.1705 0.9084 0.0569 0.0000 -0.0173 0.2013 0.269 + 40 -3.7613 5.1351 3.4440 4.8152 0.0968 1.2164 0.9440 0.0461 0.0000 -0.0192 0.2097 0.270 + 41 -4.4532 4.6522 3.3149 4.6264 0.0802 1.2947 1.0048 0.0286 0.0000 -0.0187 0.2210 0.269 + 42 -5.1831 4.1429 3.0930 4.3460 0.0545 1.3709 1.0639 0.0073 0.0000 -0.0199 0.2333 0.269 + 43 -6.0123 3.7903 3.4706 4.0673 0.0370 1.3395 1.0900 -0.0016 0.0000 -0.0146 0.2575 0.263 + 44 -6.9353 3.6075 3.3775 3.8474 0.0336 1.3307 1.0828 0.0013 0.0000 -0.0147 0.2561 0.264 + 45 -7.8737 3.4215 3.2389 3.6476 0.0278 1.3302 1.0824 0.0011 0.0000 -0.0145 0.2558 0.263 + 46 -8.8172 3.2345 3.0619 3.4565 0.0240 1.3337 1.0852 -0.0001 0.0000 -0.0142 0.2561 0.263 + 47 -9.7556 3.0486 2.8543 3.2671 0.0231 1.3378 1.0885 -0.0015 0.0000 -0.0139 0.2565 0.263 + 48 -10.6786 2.8657 2.6239 3.0807 0.0242 1.3422 1.0921 -0.0027 0.0000 -0.0135 0.2570 0.262 + 49 -11.5760 2.6879 2.3787 2.8957 0.0265 1.3453 1.0947 -0.0040 0.0000 -0.0130 0.2570 0.262 + 50 -12.4328 2.5181 2.1010 2.7124 0.0299 1.3454 1.0947 -0.0052 0.0000 -0.0122 0.2563 0.261 + 51 -13.2400 2.3582 1.8520 2.5294 0.0347 1.3399 1.0903 -0.0060 0.0000 -0.0110 0.2542 0.260 + 52 -13.9941 2.2087 1.6074 2.3438 0.0415 1.3257 1.0787 -0.0065 0.0000 -0.0092 0.2500 0.258 + 53 -14.6868 2.0715 1.3716 2.1502 0.0509 1.2968 1.0552 -0.0064 0.0000 -0.0062 0.2422 0.256 + 54 -15.3105 1.9479 1.1479 1.9417 0.0629 1.2452 1.0132 -0.0055 0.0000 -0.0019 0.2290 0.252 + 55 -15.8583 1.8393 0.9381 1.7073 0.0765 1.1589 0.9430 -0.0026 0.0000 0.0024 0.2095 0.247 + 56 -16.3244 1.7470 0.7427 1.4376 0.0901 1.0250 0.8340 0.0089 0.0000 -0.0001 0.1877 0.250 + 57 -16.6722 1.4928 0.4131 1.1450 0.1046 2.5707 0.7857 -0.0366 0.0000 -0.0041 0.1003 0.255 + 58 -16.9098 1.1466 0.2292 0.8482 0.1247 2.5083 0.7666 -0.0844 0.0000 0.0253 0.0835 0.217 + 59 -17.0696 0.9138 0.1104 0.5239 0.1410 1.9777 0.6044 -0.1218 0.0000 0.0526 0.0499 0.163 + 60 -17.1499 0.7967 0.0322 0.1774 0.1499 0.7954 0.2431 -0.0932 0.0000 0.0332 0.0136 0.114 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06425 Clsurf = -0.00661 - CYsurf = -0.01011 Cmsurf = -0.31524 - CDsurf = 0.00653 Cnsurf = 0.00533 - CDisurf = 0.00653 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06411 Clsurf = -0.00660 + CYsurf = -0.01009 Cmsurf = -0.31457 + CDsurf = 0.00651 Cnsurf = 0.00532 + CDisurf = 0.00651 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39144 CDsurf = 0.03930 + CLsurf = 0.39059 CDsurf = 0.03921 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.6580 0.1680 0.4591 0.3490 0.2552 0.0000 -0.0165 -0.0988 0.297 - 62 0.0418 4.2566 0.2392 1.3574 0.1688 0.4121 0.3133 0.0595 0.0000 -0.0166 -0.0843 0.303 - 63 0.1156 4.2274 0.3930 1.3361 0.1690 0.4112 0.3126 0.0469 0.0000 -0.0156 -0.0829 0.300 - 64 0.2254 4.1839 0.5386 1.3293 0.1685 0.4141 0.3148 0.0441 0.0000 -0.0139 -0.0819 0.294 - 65 0.3698 4.1268 0.6730 1.3279 0.1669 0.4198 0.3191 0.0428 0.0000 -0.0119 -0.0811 0.287 - 66 0.5474 4.0565 0.7936 1.3254 0.1641 0.4267 0.3244 0.0416 0.0000 -0.0097 -0.0804 0.280 - 67 0.7617 3.9717 0.9441 1.3213 0.1596 0.4348 0.3305 0.0410 0.0000 -0.0077 -0.0801 0.273 - 68 1.0116 3.8728 1.0344 1.3172 0.1532 0.4449 0.3382 0.0403 0.0000 -0.0058 -0.0801 0.267 - 69 1.2891 3.7630 1.1046 1.3096 0.1451 0.4555 0.3462 0.0401 0.0000 -0.0043 -0.0806 0.262 - 70 1.5912 3.6435 1.1542 1.3015 0.1359 0.4679 0.3556 0.0398 0.0000 -0.0030 -0.0816 0.258 - 71 1.9146 3.5155 1.1831 1.2915 0.1266 0.4815 0.3660 0.0398 0.0000 -0.0019 -0.0829 0.255 - 72 2.2558 3.3805 1.1921 1.2778 0.1185 0.4957 0.3767 0.0396 0.0000 -0.0010 -0.0845 0.253 - 73 2.6109 3.2400 1.1821 1.2640 0.1121 0.5118 0.3890 0.0398 0.0000 -0.0002 -0.0865 0.250 - 74 2.9762 3.0955 1.1548 1.2466 0.1075 0.5286 0.4018 0.0400 0.0000 0.0005 -0.0887 0.249 - 75 3.3476 2.9485 1.1122 1.2272 0.1043 0.5467 0.4155 0.0398 0.0000 0.0013 -0.0911 0.247 - 76 3.7210 2.8008 1.0564 1.2049 0.1022 0.5654 0.4297 0.0399 0.0000 0.0021 -0.0935 0.245 - 77 4.0924 2.6538 0.9900 1.1777 0.1011 0.5836 0.4436 0.0397 0.0000 0.0029 -0.0958 0.243 - 78 4.4577 2.5093 0.9155 1.1468 0.1007 0.6013 0.4570 0.0394 0.0000 0.0040 -0.0979 0.241 - 79 4.8128 2.3687 0.8353 1.1095 0.1012 0.6167 0.4687 0.0386 0.0000 0.0052 -0.0994 0.239 - 80 5.1540 2.2338 0.7518 1.0666 0.1026 0.6290 0.4781 0.0379 0.0000 0.0068 -0.1000 0.236 - 81 5.4774 2.1058 0.6671 1.0173 0.1049 0.6368 0.4840 0.0365 0.0000 0.0089 -0.0996 0.232 - 82 5.7795 1.9862 0.5830 0.9589 0.1081 0.6368 0.4840 0.0346 0.0000 0.0114 -0.0974 0.226 - 83 6.0570 1.8764 0.5012 0.8931 0.1122 0.6283 0.4775 0.0323 0.0000 0.0146 -0.0932 0.219 - 84 6.3069 1.7776 0.4225 0.8167 0.1168 0.6069 0.4613 0.0295 0.0000 0.0184 -0.0865 0.210 - 85 6.5264 1.6907 0.3478 0.7311 0.1217 0.5716 0.4345 0.0258 0.0000 0.0224 -0.0771 0.198 - 86 6.7314 1.6096 0.3326 0.6306 0.1266 0.5184 0.3940 0.0217 0.0000 0.0262 -0.0649 0.183 - 87 6.9144 1.5372 0.2507 0.5083 0.1314 0.4380 0.3329 0.0161 0.0000 0.0285 -0.0495 0.164 - 88 7.0535 1.4822 0.1746 0.3729 0.1352 0.3338 0.2537 0.0099 0.0000 0.0269 -0.0334 0.144 - 89 7.1471 1.4451 0.1029 0.2279 0.1379 0.2097 0.1594 0.0041 0.0000 0.0197 -0.0186 0.126 + 61 0.0047 4.2713 0.0803 1.6525 0.1681 0.4576 0.3479 0.2539 0.0000 -0.0164 -0.0985 0.297 + 62 0.0418 4.2566 0.2392 1.3533 0.1688 0.4109 0.3123 0.0595 0.0000 -0.0165 -0.0840 0.303 + 63 0.1156 4.2274 0.3930 1.3314 0.1691 0.4098 0.3115 0.0468 0.0000 -0.0156 -0.0827 0.300 + 64 0.2254 4.1839 0.5386 1.3253 0.1686 0.4129 0.3139 0.0438 0.0000 -0.0139 -0.0817 0.294 + 65 0.3698 4.1268 0.6730 1.3236 0.1670 0.4185 0.3181 0.0424 0.0000 -0.0119 -0.0809 0.287 + 66 0.5474 4.0565 0.7936 1.3207 0.1642 0.4251 0.3232 0.0418 0.0000 -0.0097 -0.0802 0.280 + 67 0.7617 3.9717 0.9441 1.3179 0.1597 0.4337 0.3297 0.0410 0.0000 -0.0077 -0.0799 0.273 + 68 1.0116 3.8728 1.0344 1.3117 0.1533 0.4431 0.3368 0.0401 0.0000 -0.0058 -0.0799 0.267 + 69 1.2891 3.7630 1.1046 1.3061 0.1452 0.4544 0.3454 0.0398 0.0000 -0.0043 -0.0804 0.262 + 70 1.5912 3.6435 1.1542 1.2978 0.1360 0.4666 0.3546 0.0397 0.0000 -0.0030 -0.0814 0.258 + 71 1.9146 3.5155 1.1831 1.2873 0.1268 0.4799 0.3647 0.0397 0.0000 -0.0019 -0.0827 0.255 + 72 2.2558 3.3805 1.1921 1.2744 0.1186 0.4943 0.3757 0.0397 0.0000 -0.0010 -0.0843 0.253 + 73 2.6109 3.2400 1.1821 1.2605 0.1122 0.5104 0.3879 0.0399 0.0000 -0.0002 -0.0863 0.251 + 74 2.9762 3.0955 1.1548 1.2443 0.1076 0.5276 0.4010 0.0401 0.0000 0.0005 -0.0886 0.249 + 75 3.3476 2.9485 1.1122 1.2246 0.1044 0.5455 0.4146 0.0399 0.0000 0.0013 -0.0909 0.247 + 76 3.7210 2.8008 1.0564 1.2017 0.1023 0.5638 0.4286 0.0399 0.0000 0.0020 -0.0933 0.245 + 77 4.0924 2.6538 0.9900 1.1755 0.1011 0.5825 0.4427 0.0396 0.0000 0.0029 -0.0957 0.243 + 78 4.4577 2.5093 0.9155 1.1447 0.1008 0.6003 0.4563 0.0392 0.0000 0.0040 -0.0977 0.241 + 79 4.8128 2.3687 0.8353 1.1082 0.1012 0.6160 0.4682 0.0385 0.0000 0.0052 -0.0992 0.239 + 80 5.1540 2.2338 0.7518 1.0656 0.1026 0.6285 0.4777 0.0377 0.0000 0.0068 -0.1000 0.236 + 81 5.4774 2.1058 0.6671 1.0160 0.1049 0.6360 0.4834 0.0365 0.0000 0.0089 -0.0995 0.232 + 82 5.7795 1.9862 0.5830 0.9578 0.1082 0.6361 0.4835 0.0342 0.0000 0.0114 -0.0973 0.226 + 83 6.0570 1.8764 0.5012 0.8923 0.1122 0.6276 0.4771 0.0323 0.0000 0.0146 -0.0931 0.219 + 84 6.3069 1.7776 0.4225 0.8166 0.1169 0.6068 0.4612 0.0296 0.0000 0.0184 -0.0864 0.210 + 85 6.5264 1.6907 0.3478 0.7311 0.1217 0.5716 0.4345 0.0257 0.0000 0.0224 -0.0771 0.198 + 86 6.7314 1.6096 0.3326 0.6304 0.1267 0.5182 0.3938 0.0216 0.0000 0.0262 -0.0649 0.183 + 87 6.9144 1.5372 0.2507 0.5079 0.1314 0.4376 0.3326 0.0161 0.0000 0.0285 -0.0495 0.164 + 88 7.0535 1.4822 0.1746 0.3729 0.1352 0.3338 0.2537 0.0100 0.0000 0.0269 -0.0334 0.144 + 89 7.1471 1.4451 0.1029 0.2278 0.1379 0.2097 0.1593 0.0041 0.0000 0.0197 -0.0185 0.126 90 7.1941 1.4265 0.0340 0.0767 0.1393 0.0722 0.0549 -0.0018 0.0000 0.0073 -0.0058 0.117 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06425 Clsurf = 0.00661 - CYsurf = 0.01011 Cmsurf = -0.31524 - CDsurf = 0.00653 Cnsurf = -0.00533 - CDisurf = 0.00653 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06411 Clsurf = 0.00660 + CYsurf = 0.01009 Cmsurf = -0.31457 + CDsurf = 0.00651 Cnsurf = -0.00532 + CDisurf = 0.00651 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39144 CDsurf = 0.03930 + CLsurf = 0.39059 CDsurf = 0.03921 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.6580 0.1681 0.4591 0.3490 0.2552 0.0000 -0.0165 0.0988 0.297 - 92 -0.0418 4.2566 0.2392 1.3574 0.1688 0.4121 0.3133 0.0595 0.0000 -0.0166 0.0843 0.303 - 93 -0.1156 4.2274 0.3930 1.3361 0.1690 0.4112 0.3126 0.0469 0.0000 -0.0156 0.0829 0.300 - 94 -0.2254 4.1839 0.5386 1.3293 0.1685 0.4141 0.3148 0.0441 0.0000 -0.0139 0.0819 0.294 - 95 -0.3698 4.1268 0.6730 1.3279 0.1669 0.4198 0.3191 0.0428 0.0000 -0.0119 0.0811 0.287 - 96 -0.5474 4.0565 0.7936 1.3254 0.1641 0.4267 0.3244 0.0416 0.0000 -0.0097 0.0804 0.280 - 97 -0.7617 3.9717 0.9441 1.3213 0.1596 0.4348 0.3305 0.0410 0.0000 -0.0077 0.0801 0.273 - 98 -1.0116 3.8728 1.0344 1.3172 0.1532 0.4449 0.3382 0.0403 0.0000 -0.0058 0.0801 0.267 - 99 -1.2891 3.7630 1.1046 1.3096 0.1451 0.4555 0.3462 0.0401 0.0000 -0.0043 0.0806 0.262 - 100 -1.5912 3.6435 1.1542 1.3015 0.1359 0.4679 0.3556 0.0398 0.0000 -0.0030 0.0816 0.258 - 101 -1.9146 3.5155 1.1831 1.2915 0.1266 0.4815 0.3660 0.0398 0.0000 -0.0019 0.0829 0.255 - 102 -2.2558 3.3805 1.1921 1.2777 0.1185 0.4957 0.3767 0.0396 0.0000 -0.0010 0.0845 0.253 - 103 -2.6109 3.2400 1.1821 1.2640 0.1121 0.5118 0.3890 0.0398 0.0000 -0.0002 0.0865 0.250 - 104 -2.9762 3.0955 1.1548 1.2466 0.1075 0.5286 0.4018 0.0400 0.0000 0.0005 0.0887 0.249 - 105 -3.3476 2.9485 1.1122 1.2272 0.1043 0.5467 0.4155 0.0398 0.0000 0.0013 0.0911 0.247 - 106 -3.7210 2.8008 1.0564 1.2048 0.1022 0.5653 0.4297 0.0399 0.0000 0.0021 0.0935 0.245 - 107 -4.0924 2.6538 0.9900 1.1777 0.1011 0.5835 0.4435 0.0397 0.0000 0.0029 0.0958 0.243 - 108 -4.4577 2.5093 0.9155 1.1468 0.1007 0.6013 0.4570 0.0394 0.0000 0.0040 0.0979 0.241 - 109 -4.8128 2.3687 0.8353 1.1095 0.1012 0.6167 0.4687 0.0386 0.0000 0.0052 0.0994 0.239 - 110 -5.1540 2.2338 0.7518 1.0666 0.1026 0.6290 0.4781 0.0379 0.0000 0.0068 0.1000 0.236 - 111 -5.4774 2.1058 0.6671 1.0173 0.1049 0.6368 0.4840 0.0365 0.0000 0.0089 0.0996 0.232 - 112 -5.7795 1.9862 0.5830 0.9588 0.1081 0.6368 0.4840 0.0346 0.0000 0.0114 0.0974 0.226 - 113 -6.0570 1.8764 0.5012 0.8931 0.1122 0.6283 0.4775 0.0323 0.0000 0.0146 0.0932 0.219 - 114 -6.3069 1.7776 0.4225 0.8167 0.1168 0.6068 0.4613 0.0295 0.0000 0.0184 0.0865 0.210 - 115 -6.5264 1.6907 0.3478 0.7311 0.1217 0.5716 0.4345 0.0258 0.0000 0.0224 0.0771 0.198 - 116 -6.7314 1.6096 0.3326 0.6306 0.1266 0.5183 0.3939 0.0217 0.0000 0.0262 0.0649 0.183 - 117 -6.9144 1.5372 0.2507 0.5083 0.1314 0.4380 0.3329 0.0161 0.0000 0.0285 0.0495 0.164 - 118 -7.0535 1.4822 0.1746 0.3729 0.1352 0.3338 0.2537 0.0099 0.0000 0.0269 0.0334 0.144 - 119 -7.1471 1.4451 0.1029 0.2279 0.1379 0.2097 0.1594 0.0041 0.0000 0.0197 0.0186 0.126 + 91 -0.0047 4.2713 0.0803 1.6525 0.1682 0.4576 0.3479 0.2539 0.0000 -0.0164 0.0985 0.297 + 92 -0.0418 4.2566 0.2392 1.3533 0.1688 0.4109 0.3123 0.0595 0.0000 -0.0165 0.0840 0.303 + 93 -0.1156 4.2274 0.3930 1.3314 0.1691 0.4098 0.3115 0.0468 0.0000 -0.0156 0.0827 0.300 + 94 -0.2254 4.1839 0.5386 1.3253 0.1686 0.4129 0.3139 0.0438 0.0000 -0.0139 0.0817 0.294 + 95 -0.3698 4.1268 0.6730 1.3236 0.1670 0.4185 0.3181 0.0424 0.0000 -0.0119 0.0809 0.287 + 96 -0.5474 4.0565 0.7936 1.3207 0.1642 0.4251 0.3232 0.0418 0.0000 -0.0097 0.0802 0.280 + 97 -0.7617 3.9717 0.9441 1.3179 0.1597 0.4337 0.3297 0.0410 0.0000 -0.0077 0.0799 0.273 + 98 -1.0116 3.8728 1.0344 1.3117 0.1533 0.4431 0.3368 0.0401 0.0000 -0.0058 0.0799 0.267 + 99 -1.2891 3.7630 1.1046 1.3061 0.1452 0.4544 0.3454 0.0398 0.0000 -0.0043 0.0804 0.262 + 100 -1.5912 3.6435 1.1542 1.2978 0.1360 0.4666 0.3546 0.0397 0.0000 -0.0030 0.0814 0.258 + 101 -1.9146 3.5155 1.1831 1.2873 0.1268 0.4799 0.3647 0.0397 0.0000 -0.0019 0.0827 0.255 + 102 -2.2558 3.3805 1.1921 1.2744 0.1186 0.4943 0.3757 0.0397 0.0000 -0.0010 0.0843 0.253 + 103 -2.6109 3.2400 1.1821 1.2605 0.1122 0.5104 0.3879 0.0399 0.0000 -0.0002 0.0863 0.251 + 104 -2.9762 3.0955 1.1548 1.2443 0.1076 0.5276 0.4010 0.0401 0.0000 0.0005 0.0886 0.249 + 105 -3.3476 2.9485 1.1122 1.2246 0.1044 0.5455 0.4146 0.0399 0.0000 0.0013 0.0909 0.247 + 106 -3.7210 2.8008 1.0564 1.2017 0.1023 0.5638 0.4286 0.0399 0.0000 0.0020 0.0933 0.245 + 107 -4.0924 2.6538 0.9900 1.1755 0.1011 0.5825 0.4427 0.0396 0.0000 0.0029 0.0957 0.243 + 108 -4.4577 2.5093 0.9155 1.1447 0.1008 0.6003 0.4563 0.0392 0.0000 0.0040 0.0977 0.241 + 109 -4.8128 2.3687 0.8353 1.1082 0.1012 0.6160 0.4682 0.0385 0.0000 0.0052 0.0992 0.239 + 110 -5.1540 2.2338 0.7518 1.0656 0.1026 0.6285 0.4777 0.0377 0.0000 0.0068 0.1000 0.236 + 111 -5.4774 2.1058 0.6671 1.0160 0.1049 0.6360 0.4834 0.0365 0.0000 0.0089 0.0995 0.232 + 112 -5.7795 1.9862 0.5830 0.9578 0.1082 0.6361 0.4835 0.0342 0.0000 0.0114 0.0973 0.226 + 113 -6.0570 1.8764 0.5012 0.8923 0.1122 0.6276 0.4771 0.0323 0.0000 0.0146 0.0931 0.219 + 114 -6.3069 1.7776 0.4225 0.8166 0.1169 0.6068 0.4612 0.0296 0.0000 0.0184 0.0864 0.210 + 115 -6.5264 1.6907 0.3478 0.7311 0.1217 0.5716 0.4345 0.0257 0.0000 0.0224 0.0771 0.198 + 116 -6.7314 1.6096 0.3326 0.6304 0.1267 0.5182 0.3938 0.0216 0.0000 0.0262 0.0649 0.183 + 117 -6.9144 1.5372 0.2507 0.5079 0.1314 0.4376 0.3326 0.0161 0.0000 0.0285 0.0495 0.164 + 118 -7.0535 1.4822 0.1746 0.3729 0.1352 0.3338 0.2537 0.0100 0.0000 0.0269 0.0334 0.144 + 119 -7.1471 1.4451 0.1029 0.2278 0.1379 0.2097 0.1593 0.0041 0.0000 0.0197 0.0185 0.126 120 -7.1941 1.4265 0.0340 0.0767 0.1393 0.0722 0.0549 -0.0018 0.0000 0.0073 0.0058 0.117 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,67 +198,67 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.375 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.363 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.382 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.393 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.383 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.402 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.411 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.410 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.398 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.387 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.360 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.322 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.284 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.274 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.261 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.251 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.246 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.206 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.193 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.177 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.160 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.138 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.118 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.102 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.401 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.394 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.384 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.367 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.341 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.302 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.266 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.258 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.248 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.194 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.173 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.155 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.131 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.107 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.099 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01750 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.09550 - CDsurf = -0.00019 Cnsurf = -0.00000 - CDisurf = -0.00019 CDvsurf = 0.00000 + CLsurf = 0.01743 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = 0.09557 + CDsurf = -0.00020 Cnsurf = 0.00000 + CDisurf = -0.00020 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01764 CDsurf = -0.00019 + CLsurf = 0.01757 CDsurf = -0.00020 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.4044 0.2576 0.1530 0.0164 -0.0054 0.0000 0.0063 0.0003 -0.136 - 152 -1.3090 31.2096 11.6724 0.5626 0.2733 0.0667 0.0186 -0.0016 0.0000 0.0081 0.0009 -0.185 - 153 -0.9350 34.0626 12.7394 0.6116 0.2468 0.0428 0.0183 -0.0001 0.0000 0.0099 0.0018 -0.292 - 154 -0.5610 36.1619 13.5246 0.6383 0.2363 0.0292 0.0177 0.0011 0.0000 0.0107 0.0028 -0.357 - 155 -0.1870 37.5332 14.0374 0.6539 0.2349 0.0198 0.0171 0.0033 0.0000 0.0110 0.0046 -0.390 - 156 0.1870 37.5332 14.0374 0.6539 0.2349 0.0198 0.0171 0.0033 0.0000 0.0110 0.0046 -0.390 - 157 0.5610 36.1619 13.5246 0.6383 0.2363 0.0292 0.0177 0.0011 0.0000 0.0107 0.0028 -0.357 - 158 0.9350 34.0626 12.7394 0.6116 0.2468 0.0428 0.0183 -0.0001 0.0000 0.0099 0.0018 -0.292 - 159 1.3090 31.2096 11.6724 0.5626 0.2733 0.0667 0.0186 -0.0016 0.0000 0.0081 0.0009 -0.185 - 160 1.6830 26.5957 9.9468 0.4044 0.2576 0.1530 0.0164 -0.0054 0.0000 0.0063 0.0003 -0.136 + 151 -1.6830 26.5957 9.9468 0.4026 0.2576 0.1524 0.0163 -0.0054 0.0000 0.0064 0.0003 -0.139 + 152 -1.3090 31.2096 11.6724 0.5603 0.2733 0.0664 0.0185 -0.0016 0.0000 0.0081 0.0009 -0.188 + 153 -0.9350 34.0626 12.7394 0.6091 0.2470 0.0426 0.0182 -0.0001 0.0000 0.0099 0.0018 -0.295 + 154 -0.5610 36.1619 13.5246 0.6358 0.2366 0.0291 0.0177 0.0011 0.0000 0.0108 0.0028 -0.360 + 155 -0.1870 37.5332 14.0374 0.6514 0.2351 0.0197 0.0170 0.0032 0.0000 0.0110 0.0046 -0.394 + 156 0.1870 37.5332 14.0374 0.6514 0.2351 0.0197 0.0170 0.0032 0.0000 0.0110 0.0046 -0.394 + 157 0.5610 36.1619 13.5246 0.6358 0.2366 0.0291 0.0177 0.0011 0.0000 0.0108 0.0028 -0.360 + 158 0.9350 34.0626 12.7394 0.6091 0.2470 0.0426 0.0182 -0.0001 0.0000 0.0099 0.0018 -0.295 + 159 1.3090 31.2096 11.6724 0.5603 0.2733 0.0664 0.0185 -0.0016 0.0000 0.0081 0.0009 -0.188 + 160 1.6830 26.5957 9.9468 0.4026 0.2576 0.1524 0.0163 -0.0054 0.0000 0.0064 0.0003 -0.139 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 + CLsurf = 0.00000 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = 0.00000 Cnsurf = -0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.709 - 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0003 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.874 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.236 - 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.374 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.519 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.610 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.682 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.983 + 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.676 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.136 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.402 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.550 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.643 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.701 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.777 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_03_01.txt b/regression/scripts/AVL/avl_files/strip_forces_case_03_01.txt index 5e4db942b6..1b4c3b50a5 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_03_01.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_03_01.txt @@ -7,252 +7,252 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00880 Clsurf = 0.00261 - CYsurf = 0.00014 Cmsurf = 0.00383 - CDsurf = 0.00038 Cnsurf = -0.00020 - CDisurf = 0.00038 CDvsurf = 0.00000 + CLsurf = 0.00942 Clsurf = 0.00255 + CYsurf = 0.00011 Cmsurf = 0.00349 + CDsurf = 0.00039 Cnsurf = -0.00019 + CDisurf = 0.00039 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01711 CDsurf = 0.00075 + CLsurf = 0.01833 CDsurf = 0.00075 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 0.7190 0.0124 0.1202 0.0934 0.0176 0.0000 -0.0043 -0.0223 0.296 - 2 0.1025 7.6885 1.0492 0.7075 0.0115 0.1187 0.0922 0.0045 0.0000 -0.0043 -0.0222 0.296 - 3 0.2837 7.5620 1.7073 0.7030 0.0099 0.1198 0.0931 0.0035 0.0000 -0.0040 -0.0221 0.293 - 4 0.5530 7.3741 2.3052 0.6924 0.0074 0.1210 0.0941 0.0030 0.0000 -0.0036 -0.0220 0.288 - 5 0.9075 7.1267 2.8223 0.6711 0.0050 0.1214 0.0943 0.0024 0.0000 -0.0034 -0.0219 0.286 - 6 1.3432 6.8226 3.2414 0.6355 0.0058 0.1200 0.0933 0.0019 0.0000 -0.0034 -0.0217 0.286 - 7 1.8554 6.4651 3.5491 0.5822 0.0155 0.1160 0.0902 0.0014 0.0000 -0.0037 -0.0213 0.292 - 8 2.4386 6.0582 3.7368 0.5090 0.0230 0.1082 0.0841 0.0007 0.0000 -0.0046 -0.0208 0.304 - 9 3.0862 5.6062 3.8005 0.4170 0.0156 0.0958 0.0744 0.0002 0.0000 -0.0060 -0.0200 0.331 - 10 3.7613 5.1351 3.4440 0.3153 0.0058 0.0790 0.0614 -0.0002 0.0000 -0.0082 -0.0192 0.384 - 11 4.4532 4.6522 3.3149 0.2104 -0.0027 0.0582 0.0452 -0.0003 0.0000 -0.0115 -0.0186 0.504 - 12 5.1831 4.1429 3.0930 0.1026 -0.0129 0.0319 0.0248 -0.0003 0.0000 -0.0160 -0.0181 0.897 - 13 6.0123 3.7903 3.4706 0.0099 -0.0178 0.0032 0.0026 -0.0001 0.0000 -0.0198 -0.0182 - 14 6.9353 3.6075 3.3775 -0.0506 -0.0137 -0.0170 -0.0140 0.0001 0.0000 -0.0205 -0.0152 - 15 7.8737 3.4215 3.2389 -0.0929 -0.0101 -0.0330 -0.0272 0.0002 0.0000 -0.0207 -0.0124 -0.512 - 16 8.8172 3.2345 3.0619 -0.1221 -0.0077 -0.0458 -0.0378 0.0003 0.0000 -0.0207 -0.0101 -0.299 - 17 9.7556 3.0486 2.8543 -0.1416 -0.0065 -0.0564 -0.0465 0.0003 0.0000 -0.0207 -0.0082 -0.196 - 18 10.6786 2.8657 2.6240 -0.1536 -0.0060 -0.0651 -0.0536 0.0003 0.0000 -0.0207 -0.0066 -0.136 - 19 11.5760 2.6879 2.3787 -0.1597 -0.0059 -0.0722 -0.0594 0.0003 0.0000 -0.0207 -0.0053 -0.098 - 20 12.4328 2.5181 2.1010 -0.1611 -0.0060 -0.0777 -0.0640 0.0003 0.0000 -0.0207 -0.0043 -0.074 - 21 13.2400 2.3582 1.8520 -0.1587 -0.0062 -0.0817 -0.0673 0.0002 0.0000 -0.0208 -0.0037 -0.059 - 22 13.9941 2.2087 1.6074 -0.1529 -0.0065 -0.0841 -0.0693 0.0002 0.0000 -0.0210 -0.0034 -0.053 - 23 14.6868 2.0715 1.3716 -0.1440 -0.0070 -0.0844 -0.0696 0.0002 0.0000 -0.0212 -0.0035 -0.055 - 24 15.3105 1.9479 1.1479 -0.1317 -0.0076 -0.0821 -0.0676 0.0001 0.0000 -0.0215 -0.0042 -0.068 - 25 15.8583 1.8393 0.9381 -0.1155 -0.0079 -0.0763 -0.0628 0.0001 0.0000 -0.0215 -0.0052 -0.092 - 26 16.3244 1.7470 0.7427 -0.0958 -0.0079 -0.0666 -0.0548 0.0001 0.0000 -0.0197 -0.0054 -0.109 - 27 16.6722 1.4928 0.4131 -0.0743 -0.0077 -0.1642 -0.0498 -0.0006 0.0000 -0.0154 -0.0015 -0.059 - 28 16.9098 1.1466 0.2292 -0.0526 -0.0064 -0.1512 -0.0459 -0.0009 0.0000 -0.0164 -0.0025 -0.107 - 29 17.0696 0.9138 0.1104 -0.0309 -0.0045 -0.1115 -0.0338 -0.0014 0.0000 -0.0152 -0.0033 -0.200 - 30 17.1499 0.7967 0.0322 -0.0101 -0.0034 -0.0422 -0.0128 -0.0023 0.0000 -0.0073 -0.0020 -0.318 + 1 0.0114 7.7520 0.3539 0.7347 0.0123 0.1228 0.0954 0.0174 0.0000 -0.0056 -0.0238 0.309 + 2 0.1025 7.6885 1.0491 0.7229 0.0116 0.1213 0.0942 0.0045 0.0000 -0.0055 -0.0236 0.309 + 3 0.2837 7.5620 1.7073 0.7186 0.0102 0.1225 0.0952 0.0035 0.0000 -0.0053 -0.0236 0.305 + 4 0.5530 7.3741 2.3052 0.7082 0.0080 0.1238 0.0962 0.0030 0.0000 -0.0049 -0.0235 0.301 + 5 0.9075 7.1267 2.8223 0.6870 0.0056 0.1242 0.0966 0.0025 0.0000 -0.0047 -0.0234 0.299 + 6 1.3432 6.8226 3.2414 0.6510 0.0064 0.1229 0.0955 0.0020 0.0000 -0.0047 -0.0232 0.299 + 7 1.8554 6.4651 3.5491 0.5970 0.0162 0.1189 0.0924 0.0013 0.0000 -0.0049 -0.0228 0.303 + 8 2.4386 6.0582 3.7368 0.5231 0.0236 0.1112 0.0864 0.0008 0.0000 -0.0056 -0.0221 0.315 + 9 3.0862 5.6062 3.8005 0.4301 0.0165 0.0988 0.0768 0.0003 0.0000 -0.0069 -0.0212 0.340 + 10 3.7613 5.1351 3.4440 0.3261 0.0064 0.0818 0.0635 -0.0001 0.0000 -0.0087 -0.0200 0.388 + 11 4.4532 4.6522 3.3149 0.2179 -0.0027 0.0603 0.0468 -0.0003 0.0000 -0.0113 -0.0187 0.492 + 12 5.1831 4.1429 3.0930 0.1065 -0.0135 0.0331 0.0257 -0.0004 0.0000 -0.0151 -0.0175 0.836 + 13 6.0123 3.7903 3.4706 0.0124 -0.0183 0.0040 0.0033 -0.0001 0.0000 -0.0184 -0.0171 + 14 6.9353 3.6075 3.3775 -0.0486 -0.0139 -0.0163 -0.0135 0.0001 0.0000 -0.0190 -0.0139 + 15 7.8737 3.4215 3.2389 -0.0911 -0.0102 -0.0323 -0.0266 0.0002 0.0000 -0.0191 -0.0111 -0.467 + 16 8.8172 3.2345 3.0619 -0.1206 -0.0078 -0.0453 -0.0373 0.0003 0.0000 -0.0191 -0.0088 -0.262 + 17 9.7556 3.0486 2.8543 -0.1403 -0.0065 -0.0559 -0.0461 0.0003 0.0000 -0.0191 -0.0068 -0.164 + 18 10.6786 2.8657 2.6239 -0.1525 -0.0061 -0.0646 -0.0532 0.0003 0.0000 -0.0191 -0.0052 -0.108 + 19 11.5760 2.6879 2.3787 -0.1588 -0.0059 -0.0717 -0.0591 0.0003 0.0000 -0.0191 -0.0039 -0.073 + 20 12.4328 2.5181 2.1010 -0.1603 -0.0060 -0.0773 -0.0637 0.0003 0.0000 -0.0191 -0.0029 -0.050 + 21 13.2400 2.3582 1.8520 -0.1580 -0.0062 -0.0814 -0.0670 0.0002 0.0000 -0.0192 -0.0023 -0.036 + 22 13.9941 2.2087 1.6074 -0.1524 -0.0066 -0.0838 -0.0690 0.0002 0.0000 -0.0193 -0.0020 -0.030 + 23 14.6868 2.0715 1.3716 -0.1437 -0.0071 -0.0842 -0.0694 0.0002 0.0000 -0.0196 -0.0021 -0.032 + 24 15.3105 1.9479 1.1479 -0.1315 -0.0076 -0.0820 -0.0676 0.0001 0.0000 -0.0199 -0.0028 -0.044 + 25 15.8583 1.8393 0.9381 -0.1156 -0.0080 -0.0763 -0.0629 0.0001 0.0000 -0.0198 -0.0038 -0.065 + 26 16.3244 1.7470 0.7427 -0.0962 -0.0082 -0.0669 -0.0551 0.0001 0.0000 -0.0181 -0.0039 -0.078 + 27 16.6722 1.4928 0.4131 -0.0747 -0.0081 -0.1651 -0.0501 -0.0006 0.0000 -0.0141 -0.0009 -0.031 + 28 16.9098 1.1466 0.2292 -0.0527 -0.0065 -0.1516 -0.0460 -0.0009 0.0000 -0.0154 -0.0020 -0.084 + 29 17.0696 0.9138 0.1104 -0.0309 -0.0043 -0.1115 -0.0338 -0.0013 0.0000 -0.0146 -0.0030 -0.182 + 30 17.1499 0.7967 0.0322 -0.0101 -0.0027 -0.0419 -0.0127 -0.0021 0.0000 -0.0071 -0.0019 -0.307 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00880 Clsurf = -0.00261 - CYsurf = -0.00014 Cmsurf = 0.00383 - CDsurf = 0.00038 Cnsurf = 0.00020 - CDisurf = 0.00038 CDvsurf = 0.00000 + CLsurf = 0.00942 Clsurf = -0.00255 + CYsurf = -0.00011 Cmsurf = 0.00349 + CDsurf = 0.00039 Cnsurf = 0.00019 + CDisurf = 0.00039 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01711 CDsurf = 0.00075 + CLsurf = 0.01833 CDsurf = 0.00075 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 0.7190 0.0123 0.1202 0.0934 0.0176 0.0000 -0.0043 0.0223 0.296 - 32 -0.1025 7.6885 1.0492 0.7075 0.0115 0.1187 0.0922 0.0045 0.0000 -0.0043 0.0222 0.296 - 33 -0.2837 7.5620 1.7073 0.7030 0.0099 0.1198 0.0931 0.0035 0.0000 -0.0040 0.0221 0.293 - 34 -0.5530 7.3741 2.3052 0.6924 0.0074 0.1210 0.0941 0.0030 0.0000 -0.0036 0.0220 0.288 - 35 -0.9075 7.1267 2.8223 0.6711 0.0050 0.1214 0.0943 0.0024 0.0000 -0.0034 0.0219 0.286 - 36 -1.3432 6.8226 3.2414 0.6355 0.0058 0.1200 0.0933 0.0019 0.0000 -0.0034 0.0217 0.286 - 37 -1.8554 6.4651 3.5491 0.5821 0.0155 0.1160 0.0901 0.0014 0.0000 -0.0037 0.0213 0.292 - 38 -2.4386 6.0582 3.7368 0.5090 0.0230 0.1082 0.0841 0.0007 0.0000 -0.0046 0.0208 0.304 - 39 -3.0862 5.6062 3.8005 0.4170 0.0156 0.0958 0.0744 0.0002 0.0000 -0.0060 0.0200 0.331 - 40 -3.7613 5.1351 3.4440 0.3153 0.0058 0.0790 0.0614 -0.0002 0.0000 -0.0082 0.0192 0.384 - 41 -4.4532 4.6522 3.3149 0.2104 -0.0027 0.0582 0.0452 -0.0003 0.0000 -0.0115 0.0186 0.504 - 42 -5.1831 4.1429 3.0930 0.1026 -0.0129 0.0319 0.0248 -0.0003 0.0000 -0.0160 0.0181 0.897 - 43 -6.0123 3.7903 3.4706 0.0099 -0.0178 0.0032 0.0026 -0.0001 0.0000 -0.0198 0.0182 - 44 -6.9353 3.6075 3.3775 -0.0506 -0.0137 -0.0170 -0.0140 0.0001 0.0000 -0.0205 0.0152 - 45 -7.8737 3.4215 3.2389 -0.0929 -0.0101 -0.0330 -0.0272 0.0002 0.0000 -0.0207 0.0124 -0.512 - 46 -8.8172 3.2345 3.0619 -0.1221 -0.0077 -0.0458 -0.0378 0.0003 0.0000 -0.0207 0.0101 -0.299 - 47 -9.7556 3.0486 2.8543 -0.1416 -0.0065 -0.0564 -0.0465 0.0003 0.0000 -0.0207 0.0082 -0.196 - 48 -10.6786 2.8657 2.6240 -0.1536 -0.0060 -0.0651 -0.0536 0.0003 0.0000 -0.0207 0.0066 -0.136 - 49 -11.5760 2.6879 2.3787 -0.1597 -0.0059 -0.0722 -0.0594 0.0003 0.0000 -0.0207 0.0053 -0.098 - 50 -12.4328 2.5181 2.1010 -0.1611 -0.0060 -0.0777 -0.0640 0.0003 0.0000 -0.0207 0.0043 -0.074 - 51 -13.2400 2.3582 1.8520 -0.1587 -0.0062 -0.0817 -0.0673 0.0002 0.0000 -0.0208 0.0037 -0.059 - 52 -13.9941 2.2087 1.6074 -0.1529 -0.0065 -0.0841 -0.0693 0.0002 0.0000 -0.0210 0.0034 -0.053 - 53 -14.6868 2.0715 1.3716 -0.1440 -0.0070 -0.0844 -0.0696 0.0002 0.0000 -0.0212 0.0035 -0.055 - 54 -15.3105 1.9479 1.1479 -0.1317 -0.0076 -0.0821 -0.0676 0.0001 0.0000 -0.0215 0.0042 -0.068 - 55 -15.8583 1.8393 0.9381 -0.1155 -0.0079 -0.0763 -0.0628 0.0001 0.0000 -0.0215 0.0052 -0.092 - 56 -16.3244 1.7470 0.7427 -0.0958 -0.0079 -0.0666 -0.0548 0.0001 0.0000 -0.0197 0.0054 -0.109 - 57 -16.6722 1.4928 0.4131 -0.0743 -0.0077 -0.1642 -0.0498 -0.0006 0.0000 -0.0154 0.0015 -0.059 - 58 -16.9098 1.1466 0.2292 -0.0526 -0.0064 -0.1512 -0.0459 -0.0009 0.0000 -0.0164 0.0025 -0.107 - 59 -17.0696 0.9138 0.1104 -0.0309 -0.0045 -0.1115 -0.0338 -0.0014 0.0000 -0.0152 0.0033 -0.200 - 60 -17.1499 0.7967 0.0322 -0.0101 -0.0034 -0.0422 -0.0128 -0.0023 0.0000 -0.0073 0.0020 -0.318 + 31 -0.0114 7.7520 0.3539 0.7347 0.0123 0.1228 0.0954 0.0174 0.0000 -0.0056 0.0238 0.309 + 32 -0.1025 7.6885 1.0491 0.7229 0.0116 0.1213 0.0942 0.0045 0.0000 -0.0055 0.0236 0.309 + 33 -0.2837 7.5620 1.7073 0.7186 0.0102 0.1225 0.0952 0.0035 0.0000 -0.0053 0.0236 0.305 + 34 -0.5530 7.3741 2.3052 0.7082 0.0080 0.1238 0.0962 0.0030 0.0000 -0.0049 0.0235 0.301 + 35 -0.9075 7.1267 2.8223 0.6870 0.0056 0.1242 0.0966 0.0025 0.0000 -0.0047 0.0234 0.299 + 36 -1.3432 6.8226 3.2414 0.6510 0.0064 0.1229 0.0955 0.0020 0.0000 -0.0047 0.0232 0.299 + 37 -1.8554 6.4651 3.5491 0.5970 0.0162 0.1189 0.0924 0.0013 0.0000 -0.0049 0.0228 0.303 + 38 -2.4386 6.0582 3.7368 0.5231 0.0236 0.1112 0.0864 0.0008 0.0000 -0.0056 0.0221 0.315 + 39 -3.0862 5.6062 3.8005 0.4301 0.0165 0.0988 0.0768 0.0003 0.0000 -0.0069 0.0212 0.340 + 40 -3.7613 5.1351 3.4440 0.3261 0.0064 0.0818 0.0635 -0.0001 0.0000 -0.0087 0.0200 0.388 + 41 -4.4532 4.6522 3.3149 0.2179 -0.0027 0.0603 0.0468 -0.0003 0.0000 -0.0113 0.0187 0.492 + 42 -5.1831 4.1429 3.0930 0.1065 -0.0135 0.0331 0.0257 -0.0004 0.0000 -0.0151 0.0175 0.836 + 43 -6.0123 3.7903 3.4706 0.0124 -0.0183 0.0040 0.0033 -0.0001 0.0000 -0.0184 0.0171 + 44 -6.9353 3.6075 3.3775 -0.0486 -0.0139 -0.0163 -0.0135 0.0001 0.0000 -0.0190 0.0139 + 45 -7.8737 3.4215 3.2389 -0.0911 -0.0102 -0.0323 -0.0266 0.0002 0.0000 -0.0191 0.0111 -0.467 + 46 -8.8172 3.2345 3.0619 -0.1206 -0.0078 -0.0453 -0.0373 0.0003 0.0000 -0.0191 0.0088 -0.262 + 47 -9.7556 3.0486 2.8543 -0.1403 -0.0065 -0.0559 -0.0461 0.0003 0.0000 -0.0191 0.0068 -0.164 + 48 -10.6786 2.8657 2.6239 -0.1525 -0.0061 -0.0646 -0.0532 0.0003 0.0000 -0.0191 0.0052 -0.108 + 49 -11.5760 2.6879 2.3787 -0.1588 -0.0059 -0.0717 -0.0591 0.0003 0.0000 -0.0191 0.0039 -0.073 + 50 -12.4328 2.5181 2.1010 -0.1603 -0.0060 -0.0773 -0.0637 0.0003 0.0000 -0.0191 0.0029 -0.050 + 51 -13.2400 2.3582 1.8520 -0.1580 -0.0062 -0.0814 -0.0670 0.0002 0.0000 -0.0192 0.0023 -0.036 + 52 -13.9941 2.2087 1.6074 -0.1524 -0.0066 -0.0838 -0.0690 0.0002 0.0000 -0.0193 0.0020 -0.030 + 53 -14.6868 2.0715 1.3716 -0.1437 -0.0071 -0.0842 -0.0694 0.0002 0.0000 -0.0196 0.0021 -0.032 + 54 -15.3105 1.9479 1.1479 -0.1315 -0.0076 -0.0820 -0.0676 0.0001 0.0000 -0.0199 0.0028 -0.044 + 55 -15.8583 1.8393 0.9381 -0.1156 -0.0080 -0.0763 -0.0629 0.0001 0.0000 -0.0198 0.0038 -0.065 + 56 -16.3244 1.7470 0.7427 -0.0962 -0.0082 -0.0669 -0.0551 0.0001 0.0000 -0.0181 0.0039 -0.079 + 57 -16.6722 1.4928 0.4131 -0.0747 -0.0081 -0.1651 -0.0501 -0.0006 0.0000 -0.0141 0.0009 -0.031 + 58 -16.9098 1.1466 0.2292 -0.0527 -0.0065 -0.1516 -0.0460 -0.0009 0.0000 -0.0154 0.0020 -0.084 + 59 -17.0696 0.9138 0.1104 -0.0309 -0.0043 -0.1115 -0.0338 -0.0013 0.0000 -0.0146 0.0030 -0.182 + 60 -17.1499 0.7967 0.0322 -0.0101 -0.0027 -0.0419 -0.0127 -0.0021 0.0000 -0.0071 0.0019 -0.307 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02829 Clsurf = 0.00276 - CYsurf = 0.00455 Cmsurf = 0.13570 - CDsurf = 0.00011 Cnsurf = -0.00280 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02844 Clsurf = 0.00277 + CYsurf = 0.00458 Cmsurf = 0.13637 + CDsurf = 0.00011 Cnsurf = -0.00282 CDisurf = 0.00011 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.17249 CDsurf = 0.00069 + CLsurf = -0.17335 CDsurf = 0.00066 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.5800 -0.0208 -0.1718 -0.1340 0.0556 0.0000 0.0082 0.0353 0.311 - 62 0.0418 4.2566 0.2392 -0.6581 -0.0212 -0.1981 -0.1545 0.0067 0.0000 0.0078 0.0389 0.300 - 63 0.1156 4.2274 0.3930 -0.6641 -0.0216 -0.2014 -0.1571 0.0035 0.0000 0.0073 0.0390 0.296 - 64 0.2254 4.1839 0.5386 -0.6658 -0.0219 -0.2041 -0.1591 0.0027 0.0000 0.0065 0.0387 0.291 - 65 0.3698 4.1268 0.6730 -0.6660 -0.0219 -0.2070 -0.1614 0.0023 0.0000 0.0054 0.0383 0.284 - 66 0.5474 4.0565 0.7936 -0.6649 -0.0217 -0.2102 -0.1640 0.0018 0.0000 0.0044 0.0379 0.277 - 67 0.7617 3.9717 0.9441 -0.6634 -0.0209 -0.2142 -0.1671 0.0014 0.0000 0.0033 0.0377 0.270 - 68 1.0116 3.8728 1.0344 -0.6590 -0.0196 -0.2183 -0.1702 0.0011 0.0000 0.0023 0.0375 0.264 - 69 1.2891 3.7630 1.1046 -0.6530 -0.0176 -0.2226 -0.1736 0.0008 0.0000 0.0015 0.0375 0.259 - 70 1.5912 3.6435 1.1542 -0.6433 -0.0152 -0.2265 -0.1767 0.0005 0.0000 0.0009 0.0376 0.255 - 71 1.9146 3.5155 1.1831 -0.6309 -0.0127 -0.2302 -0.1795 0.0003 0.0000 0.0003 0.0378 0.252 - 72 2.2558 3.3805 1.1921 -0.6154 -0.0108 -0.2335 -0.1821 0.0001 0.0000 -0.0001 0.0380 0.250 - 73 2.6109 3.2400 1.1821 -0.5962 -0.0097 -0.2361 -0.1841 -0.0000 0.0000 -0.0004 0.0381 0.248 - 74 2.9762 3.0955 1.1548 -0.5744 -0.0094 -0.2381 -0.1857 -0.0001 0.0000 -0.0006 0.0383 0.247 - 75 3.3476 2.9485 1.1122 -0.5497 -0.0095 -0.2392 -0.1865 -0.0002 0.0000 -0.0008 0.0383 0.246 - 76 3.7210 2.8008 1.0564 -0.5228 -0.0100 -0.2395 -0.1868 -0.0002 0.0000 -0.0009 0.0382 0.245 - 77 4.0924 2.6538 0.9900 -0.4943 -0.0107 -0.2390 -0.1864 -0.0002 0.0000 -0.0010 0.0380 0.244 - 78 4.4577 2.5093 0.9155 -0.4645 -0.0115 -0.2375 -0.1852 -0.0002 0.0000 -0.0012 0.0376 0.243 - 79 4.8128 2.3687 0.8353 -0.4343 -0.0124 -0.2352 -0.1834 -0.0002 0.0000 -0.0015 0.0371 0.242 - 80 5.1540 2.2338 0.7518 -0.4035 -0.0134 -0.2318 -0.1808 -0.0002 0.0000 -0.0018 0.0362 0.240 - 81 5.4774 2.1058 0.6671 -0.3724 -0.0146 -0.2269 -0.1769 -0.0001 0.0000 -0.0023 0.0350 0.237 - 82 5.7795 1.9862 0.5830 -0.3412 -0.0160 -0.2204 -0.1719 -0.0002 0.0000 -0.0030 0.0333 0.232 - 83 6.0570 1.8764 0.5012 -0.3091 -0.0175 -0.2114 -0.1648 -0.0003 0.0000 -0.0039 0.0311 0.226 - 84 6.3069 1.7776 0.4225 -0.2765 -0.0191 -0.1996 -0.1557 -0.0002 0.0000 -0.0050 0.0282 0.218 - 85 6.5264 1.6907 0.3478 -0.2426 -0.0208 -0.1841 -0.1436 -0.0003 0.0000 -0.0062 0.0247 0.207 - 86 6.7314 1.6096 0.3326 -0.2052 -0.0224 -0.1636 -0.1276 -0.0003 0.0000 -0.0074 0.0204 0.192 - 87 6.9144 1.5372 0.2507 -0.1630 -0.0239 -0.1361 -0.1061 -0.0005 0.0000 -0.0081 0.0153 0.174 - 88 7.0535 1.4822 0.1746 -0.1184 -0.0252 -0.1025 -0.0799 -0.0005 0.0000 -0.0077 0.0102 0.154 - 89 7.1471 1.4451 0.1029 -0.0718 -0.0260 -0.0638 -0.0497 -0.0005 0.0000 -0.0056 0.0056 0.137 - 90 7.1941 1.4265 0.0340 -0.0241 -0.0265 -0.0217 -0.0169 -0.0005 0.0000 -0.0021 0.0018 0.126 + 61 0.0047 4.2713 0.0803 -0.5830 -0.0207 -0.1726 -0.1346 0.0562 0.0000 0.0082 0.0355 0.311 + 62 0.0418 4.2566 0.2392 -0.6621 -0.0211 -0.1993 -0.1554 0.0068 0.0000 0.0078 0.0391 0.300 + 63 0.1156 4.2274 0.3930 -0.6682 -0.0215 -0.2026 -0.1580 0.0035 0.0000 0.0073 0.0392 0.296 + 64 0.2254 4.1839 0.5386 -0.6700 -0.0218 -0.2053 -0.1601 0.0026 0.0000 0.0065 0.0389 0.290 + 65 0.3698 4.1268 0.6730 -0.6701 -0.0218 -0.2082 -0.1624 0.0022 0.0000 0.0054 0.0385 0.284 + 66 0.5474 4.0565 0.7936 -0.6694 -0.0216 -0.2116 -0.1651 0.0018 0.0000 0.0044 0.0382 0.276 + 67 0.7617 3.9717 0.9441 -0.6672 -0.0208 -0.2155 -0.1680 0.0014 0.0000 0.0033 0.0379 0.270 + 68 1.0116 3.8728 1.0344 -0.6634 -0.0195 -0.2197 -0.1714 0.0010 0.0000 0.0023 0.0378 0.264 + 69 1.2891 3.7630 1.1046 -0.6567 -0.0175 -0.2239 -0.1746 0.0007 0.0000 0.0015 0.0377 0.259 + 70 1.5912 3.6435 1.1542 -0.6473 -0.0150 -0.2279 -0.1777 0.0005 0.0000 0.0009 0.0378 0.255 + 71 1.9146 3.5155 1.1831 -0.6348 -0.0126 -0.2317 -0.1807 0.0002 0.0000 0.0003 0.0380 0.252 + 72 2.2558 3.3805 1.1921 -0.6190 -0.0107 -0.2349 -0.1832 0.0001 0.0000 -0.0001 0.0382 0.250 + 73 2.6109 3.2400 1.1821 -0.5997 -0.0096 -0.2375 -0.1852 -0.0000 0.0000 -0.0004 0.0383 0.248 + 74 2.9762 3.0955 1.1548 -0.5773 -0.0092 -0.2393 -0.1866 -0.0001 0.0000 -0.0006 0.0384 0.247 + 75 3.3476 2.9485 1.1122 -0.5524 -0.0094 -0.2404 -0.1875 -0.0002 0.0000 -0.0008 0.0385 0.246 + 76 3.7210 2.8008 1.0564 -0.5254 -0.0099 -0.2407 -0.1877 -0.0002 0.0000 -0.0009 0.0384 0.245 + 77 4.0924 2.6538 0.9900 -0.4965 -0.0106 -0.2400 -0.1872 -0.0002 0.0000 -0.0011 0.0382 0.244 + 78 4.4577 2.5093 0.9155 -0.4664 -0.0114 -0.2385 -0.1860 -0.0002 0.0000 -0.0012 0.0378 0.243 + 79 4.8128 2.3687 0.8353 -0.4359 -0.0123 -0.2361 -0.1841 -0.0002 0.0000 -0.0015 0.0372 0.242 + 80 5.1540 2.2338 0.7518 -0.4048 -0.0133 -0.2325 -0.1813 -0.0002 0.0000 -0.0018 0.0363 0.240 + 81 5.4774 2.1058 0.6671 -0.3736 -0.0145 -0.2276 -0.1775 -0.0001 0.0000 -0.0023 0.0351 0.237 + 82 5.7795 1.9862 0.5830 -0.3421 -0.0159 -0.2210 -0.1724 -0.0003 0.0000 -0.0030 0.0334 0.232 + 83 6.0570 1.8764 0.5012 -0.3100 -0.0175 -0.2120 -0.1653 -0.0002 0.0000 -0.0039 0.0312 0.226 + 84 6.3069 1.7776 0.4225 -0.2771 -0.0191 -0.2000 -0.1560 -0.0002 0.0000 -0.0050 0.0283 0.218 + 85 6.5264 1.6907 0.3478 -0.2430 -0.0208 -0.1845 -0.1438 -0.0003 0.0000 -0.0062 0.0247 0.207 + 86 6.7314 1.6096 0.3326 -0.2057 -0.0224 -0.1640 -0.1279 -0.0004 0.0000 -0.0074 0.0204 0.192 + 87 6.9144 1.5372 0.2507 -0.1634 -0.0239 -0.1364 -0.1064 -0.0005 0.0000 -0.0081 0.0153 0.174 + 88 7.0535 1.4822 0.1746 -0.1185 -0.0251 -0.1026 -0.0800 -0.0005 0.0000 -0.0077 0.0102 0.154 + 89 7.1471 1.4451 0.1029 -0.0719 -0.0260 -0.0639 -0.0498 -0.0005 0.0000 -0.0056 0.0056 0.137 + 90 7.1941 1.4265 0.0340 -0.0241 -0.0264 -0.0217 -0.0169 -0.0005 0.0000 -0.0021 0.0018 0.126 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02829 Clsurf = -0.00276 - CYsurf = -0.00455 Cmsurf = 0.13570 - CDsurf = 0.00011 Cnsurf = 0.00280 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02844 Clsurf = -0.00277 + CYsurf = -0.00458 Cmsurf = 0.13637 + CDsurf = 0.00011 Cnsurf = 0.00282 CDisurf = 0.00011 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.17248 CDsurf = 0.00068 + CLsurf = -0.17335 CDsurf = 0.00066 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.5800 -0.0208 -0.1718 -0.1340 0.0556 0.0000 0.0082 -0.0353 0.311 - 92 -0.0418 4.2566 0.2392 -0.6581 -0.0212 -0.1981 -0.1545 0.0067 0.0000 0.0078 -0.0389 0.300 - 93 -0.1156 4.2274 0.3930 -0.6641 -0.0216 -0.2014 -0.1571 0.0035 0.0000 0.0073 -0.0390 0.296 - 94 -0.2254 4.1839 0.5386 -0.6658 -0.0219 -0.2041 -0.1591 0.0027 0.0000 0.0065 -0.0387 0.291 - 95 -0.3698 4.1268 0.6730 -0.6660 -0.0219 -0.2070 -0.1614 0.0023 0.0000 0.0054 -0.0383 0.284 - 96 -0.5474 4.0565 0.7936 -0.6649 -0.0217 -0.2102 -0.1639 0.0018 0.0000 0.0044 -0.0379 0.277 - 97 -0.7617 3.9717 0.9441 -0.6634 -0.0209 -0.2142 -0.1671 0.0014 0.0000 0.0033 -0.0377 0.270 - 98 -1.0116 3.8728 1.0344 -0.6590 -0.0196 -0.2183 -0.1702 0.0011 0.0000 0.0023 -0.0375 0.264 - 99 -1.2891 3.7630 1.1046 -0.6530 -0.0176 -0.2226 -0.1736 0.0008 0.0000 0.0015 -0.0375 0.259 - 100 -1.5912 3.6435 1.1542 -0.6433 -0.0152 -0.2265 -0.1767 0.0005 0.0000 0.0009 -0.0376 0.255 - 101 -1.9146 3.5155 1.1831 -0.6309 -0.0127 -0.2302 -0.1795 0.0003 0.0000 0.0003 -0.0378 0.252 - 102 -2.2558 3.3805 1.1921 -0.6153 -0.0108 -0.2335 -0.1821 0.0001 0.0000 -0.0001 -0.0380 0.250 - 103 -2.6109 3.2400 1.1821 -0.5962 -0.0097 -0.2361 -0.1841 -0.0000 0.0000 -0.0004 -0.0381 0.248 - 104 -2.9762 3.0955 1.1548 -0.5743 -0.0094 -0.2381 -0.1857 -0.0001 0.0000 -0.0006 -0.0383 0.247 - 105 -3.3476 2.9485 1.1122 -0.5497 -0.0095 -0.2392 -0.1865 -0.0002 0.0000 -0.0008 -0.0383 0.246 - 106 -3.7210 2.8008 1.0564 -0.5227 -0.0100 -0.2395 -0.1868 -0.0002 0.0000 -0.0009 -0.0382 0.245 - 107 -4.0924 2.6538 0.9900 -0.4942 -0.0107 -0.2390 -0.1864 -0.0002 0.0000 -0.0010 -0.0380 0.244 - 108 -4.4577 2.5093 0.9155 -0.4644 -0.0115 -0.2375 -0.1852 -0.0002 0.0000 -0.0012 -0.0376 0.243 - 109 -4.8128 2.3687 0.8353 -0.4343 -0.0124 -0.2352 -0.1834 -0.0002 0.0000 -0.0015 -0.0371 0.242 - 110 -5.1540 2.2338 0.7518 -0.4035 -0.0134 -0.2318 -0.1807 -0.0002 0.0000 -0.0018 -0.0362 0.240 - 111 -5.4774 2.1058 0.6671 -0.3724 -0.0146 -0.2269 -0.1769 -0.0001 0.0000 -0.0023 -0.0350 0.237 - 112 -5.7795 1.9862 0.5830 -0.3412 -0.0160 -0.2204 -0.1719 -0.0002 0.0000 -0.0030 -0.0333 0.232 - 113 -6.0570 1.8764 0.5012 -0.3091 -0.0175 -0.2114 -0.1648 -0.0003 0.0000 -0.0039 -0.0311 0.226 - 114 -6.3069 1.7776 0.4225 -0.2765 -0.0191 -0.1996 -0.1557 -0.0002 0.0000 -0.0050 -0.0282 0.218 - 115 -6.5264 1.6907 0.3478 -0.2426 -0.0208 -0.1841 -0.1436 -0.0003 0.0000 -0.0062 -0.0247 0.207 - 116 -6.7314 1.6096 0.3326 -0.2052 -0.0224 -0.1636 -0.1276 -0.0003 0.0000 -0.0074 -0.0204 0.192 - 117 -6.9144 1.5372 0.2507 -0.1630 -0.0239 -0.1361 -0.1061 -0.0005 0.0000 -0.0081 -0.0153 0.174 - 118 -7.0535 1.4822 0.1746 -0.1184 -0.0252 -0.1025 -0.0799 -0.0005 0.0000 -0.0077 -0.0102 0.154 - 119 -7.1471 1.4451 0.1029 -0.0718 -0.0260 -0.0638 -0.0497 -0.0005 0.0000 -0.0056 -0.0056 0.137 - 120 -7.1941 1.4265 0.0340 -0.0241 -0.0265 -0.0217 -0.0169 -0.0005 0.0000 -0.0021 -0.0018 0.126 + 91 -0.0047 4.2713 0.0803 -0.5830 -0.0207 -0.1726 -0.1346 0.0562 0.0000 0.0082 -0.0355 0.311 + 92 -0.0418 4.2566 0.2392 -0.6621 -0.0211 -0.1993 -0.1554 0.0068 0.0000 0.0078 -0.0391 0.300 + 93 -0.1156 4.2274 0.3930 -0.6682 -0.0215 -0.2026 -0.1580 0.0035 0.0000 0.0073 -0.0392 0.296 + 94 -0.2254 4.1839 0.5386 -0.6700 -0.0218 -0.2053 -0.1601 0.0026 0.0000 0.0065 -0.0389 0.290 + 95 -0.3698 4.1268 0.6730 -0.6701 -0.0218 -0.2082 -0.1624 0.0022 0.0000 0.0054 -0.0385 0.284 + 96 -0.5474 4.0565 0.7936 -0.6694 -0.0216 -0.2116 -0.1651 0.0018 0.0000 0.0044 -0.0382 0.276 + 97 -0.7617 3.9717 0.9441 -0.6672 -0.0208 -0.2155 -0.1680 0.0014 0.0000 0.0033 -0.0379 0.270 + 98 -1.0116 3.8728 1.0344 -0.6634 -0.0195 -0.2197 -0.1714 0.0010 0.0000 0.0023 -0.0378 0.264 + 99 -1.2891 3.7630 1.1046 -0.6567 -0.0175 -0.2239 -0.1746 0.0007 0.0000 0.0015 -0.0377 0.259 + 100 -1.5912 3.6435 1.1542 -0.6473 -0.0150 -0.2279 -0.1777 0.0005 0.0000 0.0009 -0.0378 0.255 + 101 -1.9146 3.5155 1.1831 -0.6348 -0.0126 -0.2317 -0.1807 0.0002 0.0000 0.0003 -0.0380 0.252 + 102 -2.2558 3.3805 1.1921 -0.6190 -0.0107 -0.2349 -0.1832 0.0001 0.0000 -0.0001 -0.0382 0.250 + 103 -2.6109 3.2400 1.1821 -0.5997 -0.0096 -0.2375 -0.1852 -0.0000 0.0000 -0.0004 -0.0383 0.248 + 104 -2.9762 3.0955 1.1548 -0.5773 -0.0092 -0.2393 -0.1866 -0.0001 0.0000 -0.0006 -0.0384 0.247 + 105 -3.3476 2.9485 1.1122 -0.5524 -0.0094 -0.2404 -0.1875 -0.0002 0.0000 -0.0008 -0.0385 0.246 + 106 -3.7210 2.8008 1.0564 -0.5254 -0.0099 -0.2407 -0.1877 -0.0002 0.0000 -0.0009 -0.0384 0.245 + 107 -4.0924 2.6538 0.9900 -0.4965 -0.0106 -0.2400 -0.1872 -0.0002 0.0000 -0.0011 -0.0382 0.244 + 108 -4.4577 2.5093 0.9155 -0.4664 -0.0114 -0.2385 -0.1860 -0.0002 0.0000 -0.0012 -0.0378 0.243 + 109 -4.8128 2.3687 0.8353 -0.4359 -0.0123 -0.2361 -0.1841 -0.0002 0.0000 -0.0015 -0.0372 0.242 + 110 -5.1540 2.2338 0.7518 -0.4048 -0.0133 -0.2325 -0.1813 -0.0002 0.0000 -0.0018 -0.0363 0.240 + 111 -5.4774 2.1058 0.6671 -0.3736 -0.0145 -0.2276 -0.1775 -0.0001 0.0000 -0.0023 -0.0351 0.237 + 112 -5.7795 1.9862 0.5830 -0.3421 -0.0159 -0.2210 -0.1724 -0.0003 0.0000 -0.0030 -0.0334 0.232 + 113 -6.0570 1.8764 0.5012 -0.3100 -0.0175 -0.2120 -0.1653 -0.0002 0.0000 -0.0039 -0.0312 0.226 + 114 -6.3069 1.7776 0.4225 -0.2771 -0.0191 -0.2000 -0.1560 -0.0002 0.0000 -0.0050 -0.0283 0.218 + 115 -6.5264 1.6907 0.3478 -0.2430 -0.0208 -0.1844 -0.1438 -0.0003 0.0000 -0.0062 -0.0247 0.207 + 116 -6.7314 1.6096 0.3326 -0.2057 -0.0224 -0.1640 -0.1279 -0.0004 0.0000 -0.0074 -0.0204 0.192 + 117 -6.9144 1.5372 0.2507 -0.1634 -0.0239 -0.1364 -0.1064 -0.0005 0.0000 -0.0081 -0.0153 0.174 + 118 -7.0535 1.4822 0.1746 -0.1185 -0.0251 -0.1026 -0.0800 -0.0005 0.0000 -0.0077 -0.0102 0.154 + 119 -7.1471 1.4451 0.1029 -0.0719 -0.0260 -0.0639 -0.0498 -0.0005 0.0000 -0.0056 -0.0056 0.137 + 120 -7.1941 1.4265 0.0340 -0.0241 -0.0264 -0.0217 -0.0169 -0.0005 0.0000 -0.0021 -0.0018 0.126 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 - CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = -0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = 0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + Surface area = 34.910358 Ave. chord = 4.190919 + CLsurf = 0.00000 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = -0.00000 + CDsurf = -0.00000 Cnsurf = 0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00000 CDsurf = 0.00000 + CLsurf = 0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.800 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.793 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.774 - 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.754 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.728 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.700 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.660 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.611 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.555 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.486 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.427 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.401 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.371 + 121 0.0000 10.0347 0.6931 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.775 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.767 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.758 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.740 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.720 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.681 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.651 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.604 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.552 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.482 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.433 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.404 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.379 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.352 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.333 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.315 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.303 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.316 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.304 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.290 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.282 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.274 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.278 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.276 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.267 - 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.263 - 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.252 - 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.243 - 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.234 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.217 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.201 - 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.182 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.163 - 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.153 + 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.257 + 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.254 + 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.244 + 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.231 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.214 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.198 + 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.174 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.159 + 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.140 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00972 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.02412 - CDsurf = 0.00022 Cnsurf = 0.00000 + CLsurf = -0.00978 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.02405 + CDsurf = 0.00022 Cnsurf = -0.00000 CDisurf = 0.00022 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00980 CDsurf = 0.00022 + CLsurf = -0.00986 CDsurf = 0.00022 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.2429 -0.0597 -0.1136 -0.0091 0.0001 0.0000 -0.0004 0.0003 0.209 - 152 -1.3090 31.2096 11.6724 -0.3269 -0.0554 -0.0407 -0.0105 0.0002 0.0000 -0.0008 0.0004 0.172 - 153 -0.9350 34.0626 12.7394 -0.3471 -0.0333 -0.0249 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.092 - 154 -0.5610 36.1619 13.5246 -0.3520 -0.0217 -0.0163 -0.0097 0.0003 0.0000 -0.0021 0.0001 0.034 - 155 -0.1870 37.5332 14.0374 -0.3532 -0.0172 -0.0109 -0.0094 0.0003 0.0000 -0.0023 0.0000 0.006 - 156 0.1870 37.5332 14.0374 -0.3532 -0.0172 -0.0109 -0.0094 0.0003 0.0000 -0.0023 0.0000 0.006 - 157 0.5610 36.1619 13.5246 -0.3520 -0.0217 -0.0163 -0.0097 0.0003 0.0000 -0.0021 0.0001 0.034 - 158 0.9350 34.0626 12.7394 -0.3471 -0.0333 -0.0249 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.092 - 159 1.3090 31.2096 11.6724 -0.3269 -0.0554 -0.0407 -0.0105 0.0002 0.0000 -0.0008 0.0004 0.172 - 160 1.6830 26.5957 9.9468 -0.2429 -0.0597 -0.1136 -0.0091 0.0001 0.0000 -0.0004 0.0003 0.209 + 151 -1.6830 26.5957 9.9468 -0.2446 -0.0597 -0.1144 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.212 + 152 -1.3090 31.2096 11.6724 -0.3292 -0.0553 -0.0410 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.174 + 153 -0.9350 34.0626 12.7394 -0.3496 -0.0331 -0.0250 -0.0103 0.0002 0.0000 -0.0016 0.0003 0.095 + 154 -0.5610 36.1619 13.5246 -0.3545 -0.0215 -0.0164 -0.0098 0.0003 0.0000 -0.0021 0.0002 0.038 + 155 -0.1870 37.5332 14.0374 -0.3556 -0.0169 -0.0110 -0.0095 0.0003 0.0000 -0.0023 0.0001 0.009 + 156 0.1870 37.5332 14.0374 -0.3556 -0.0169 -0.0110 -0.0095 0.0003 0.0000 -0.0023 0.0001 0.009 + 157 0.5610 36.1619 13.5246 -0.3545 -0.0215 -0.0164 -0.0098 0.0003 0.0000 -0.0021 0.0002 0.038 + 158 0.9350 34.0626 12.7394 -0.3496 -0.0331 -0.0250 -0.0103 0.0002 0.0000 -0.0016 0.0003 0.095 + 159 1.3090 31.2096 11.6724 -0.3292 -0.0553 -0.0410 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.174 + 160 1.6830 26.5957 9.9468 -0.2446 -0.0597 -0.1144 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.212 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.880 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.849 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.844 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.834 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.828 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.807 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.786 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.738 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.613 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.404 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.897 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.841 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.838 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.827 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.828 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.800 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.765 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.700 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.533 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_03_02.txt b/regression/scripts/AVL/avl_files/strip_forces_case_03_02.txt index e5e63ed812..78ef412630 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_03_02.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_03_02.txt @@ -7,275 +7,275 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09194 Clsurf = -0.01467 - CYsurf = -0.00625 Cmsurf = -0.07352 - CDsurf = 0.00125 Cnsurf = 0.00069 - CDisurf = 0.00125 CDvsurf = 0.00000 + CLsurf = 0.09257 Clsurf = -0.01473 + CYsurf = -0.00625 Cmsurf = -0.07386 + CDsurf = 0.00122 Cnsurf = 0.00069 + CDisurf = 0.00122 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.17987 CDsurf = 0.00244 + CLsurf = 0.18109 CDsurf = 0.00238 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 1.6056 0.0485 0.2670 0.2071 0.0757 0.0000 -0.0106 -0.0509 0.301 - 2 0.1025 7.6885 1.0492 1.5557 0.0478 0.2609 0.2023 0.0168 0.0000 -0.0106 -0.0499 0.303 - 3 0.2837 7.5620 1.7073 1.5480 0.0461 0.2639 0.2047 0.0130 0.0000 -0.0099 -0.0498 0.298 - 4 0.5530 7.3741 2.3052 1.5358 0.0436 0.2685 0.2083 0.0114 0.0000 -0.0088 -0.0496 0.292 - 5 0.9075 7.1267 2.8223 1.5118 0.0404 0.2735 0.2121 0.0097 0.0000 -0.0077 -0.0495 0.287 - 6 1.3432 6.8226 3.2414 1.4715 0.0382 0.2781 0.2157 0.0083 0.0000 -0.0070 -0.0496 0.282 - 7 1.8554 6.4651 3.5491 1.4110 0.0401 0.2814 0.2182 0.0070 0.0000 -0.0066 -0.0499 0.280 - 8 2.4386 6.0582 3.7368 1.3260 0.0402 0.2822 0.2189 0.0046 0.0000 -0.0069 -0.0502 0.282 - 9 3.0862 5.6062 3.8005 1.2187 0.0314 0.2803 0.2174 0.0029 0.0000 -0.0080 -0.0508 0.287 - 10 3.7613 5.1351 3.4440 1.0971 0.0212 0.2755 0.2136 0.0009 0.0000 -0.0099 -0.0516 0.297 - 11 4.4532 4.6522 3.3149 0.9690 0.0114 0.2686 0.2083 -0.0006 0.0000 -0.0130 -0.0530 0.312 - 12 5.1831 4.1429 3.0930 0.8332 -0.0014 0.2593 0.2011 -0.0023 0.0000 -0.0172 -0.0550 0.335 - 13 6.0123 3.7903 3.4706 0.7117 -0.0084 0.2287 0.1878 -0.0028 0.0000 -0.0202 -0.0596 0.357 - 14 6.9353 3.6075 3.3775 0.6248 -0.0056 0.2109 0.1732 -0.0020 0.0000 -0.0207 -0.0569 0.370 - 15 7.8737 3.4215 3.2389 0.5555 -0.0036 0.1977 0.1624 -0.0015 0.0000 -0.0209 -0.0546 0.378 - 16 8.8172 3.2345 3.0619 0.4982 -0.0022 0.1876 0.1540 -0.0013 0.0000 -0.0208 -0.0527 0.385 - 17 9.7556 3.0486 2.8543 0.4496 -0.0014 0.1796 0.1475 -0.0011 0.0000 -0.0208 -0.0512 0.391 - 18 10.6786 2.8657 2.6240 0.4075 -0.0008 0.1732 0.1422 -0.0009 0.0000 -0.0207 -0.0500 0.396 - 19 11.5760 2.6879 2.3787 0.3704 -0.0003 0.1678 0.1378 -0.0008 0.0000 -0.0206 -0.0489 0.400 - 20 12.4328 2.5181 2.1010 0.3375 0.0002 0.1633 0.1340 -0.0007 0.0000 -0.0205 -0.0480 0.403 - 21 13.2400 2.3582 1.8520 0.3078 0.0009 0.1590 0.1305 -0.0006 0.0000 -0.0204 -0.0471 0.406 - 22 13.9941 2.2087 1.6074 0.2803 0.0017 0.1546 0.1269 -0.0006 0.0000 -0.0202 -0.0461 0.409 - 23 14.6868 2.0715 1.3716 0.2541 0.0029 0.1494 0.1227 -0.0005 0.0000 -0.0198 -0.0449 0.412 - 24 15.3105 1.9479 1.1479 0.2280 0.0044 0.1426 0.1171 -0.0004 0.0000 -0.0193 -0.0431 0.415 - 25 15.8583 1.8393 0.9381 0.2006 0.0064 0.1328 0.1090 -0.0003 0.0000 -0.0184 -0.0406 0.419 - 26 16.3244 1.7470 0.7427 0.1701 0.0087 0.1186 0.0974 -0.0002 0.0000 -0.0173 -0.0370 0.428 - 27 16.6722 1.4928 0.4131 0.1374 0.0113 0.3072 0.0920 -0.0005 0.0000 -0.0146 -0.0176 0.408 - 28 16.9098 1.1466 0.2292 0.1037 0.0158 0.3019 0.0904 -0.0010 0.0000 -0.0102 -0.0153 0.363 - 29 17.0696 0.9138 0.1104 0.0653 0.0200 0.2386 0.0715 -0.0013 0.0000 -0.0043 -0.0104 0.310 - 30 17.1499 0.7967 0.0322 0.0224 0.0223 0.0937 0.0281 -0.0011 0.0000 -0.0006 -0.0036 0.271 + 1 0.0114 7.7520 0.3539 1.6219 0.0484 0.2698 0.2092 0.0756 0.0000 -0.0120 -0.0524 0.307 + 2 0.1025 7.6885 1.0491 1.5712 0.0478 0.2635 0.2044 0.0168 0.0000 -0.0119 -0.0513 0.308 + 3 0.2837 7.5620 1.7073 1.5636 0.0465 0.2666 0.2068 0.0129 0.0000 -0.0112 -0.0512 0.304 + 4 0.5530 7.3741 2.3052 1.5514 0.0441 0.2712 0.2104 0.0111 0.0000 -0.0101 -0.0511 0.298 + 5 0.9075 7.1267 2.8223 1.5276 0.0410 0.2764 0.2144 0.0098 0.0000 -0.0091 -0.0511 0.292 + 6 1.3432 6.8226 3.2414 1.4868 0.0388 0.2810 0.2179 0.0081 0.0000 -0.0082 -0.0511 0.288 + 7 1.8554 6.4651 3.5491 1.4251 0.0407 0.2842 0.2204 0.0059 0.0000 -0.0078 -0.0513 0.286 + 8 2.4386 6.0582 3.7368 1.3403 0.0409 0.2852 0.2212 0.0048 0.0000 -0.0080 -0.0516 0.286 + 9 3.0862 5.6062 3.8005 1.2318 0.0323 0.2833 0.2197 0.0030 0.0000 -0.0088 -0.0520 0.290 + 10 3.7613 5.1351 3.4440 1.1075 0.0218 0.2781 0.2157 0.0013 0.0000 -0.0105 -0.0525 0.299 + 11 4.4532 4.6522 3.3149 0.9777 0.0114 0.2710 0.2102 -0.0007 0.0000 -0.0127 -0.0532 0.311 + 12 5.1831 4.1429 3.0930 0.8370 -0.0020 0.2605 0.2020 -0.0025 0.0000 -0.0162 -0.0544 0.330 + 13 6.0123 3.7903 3.4706 0.7143 -0.0089 0.2295 0.1885 -0.0028 0.0000 -0.0187 -0.0585 0.349 + 14 6.9353 3.6075 3.3775 0.6269 -0.0058 0.2116 0.1738 -0.0020 0.0000 -0.0192 -0.0557 0.360 + 15 7.8737 3.4215 3.2389 0.5573 -0.0037 0.1984 0.1629 -0.0015 0.0000 -0.0193 -0.0533 0.368 + 16 8.8172 3.2345 3.0619 0.4997 -0.0023 0.1882 0.1545 -0.0013 0.0000 -0.0192 -0.0514 0.374 + 17 9.7556 3.0486 2.8543 0.4509 -0.0014 0.1801 0.1479 -0.0011 0.0000 -0.0191 -0.0499 0.379 + 18 10.6786 2.8657 2.6239 0.4086 -0.0009 0.1736 0.1426 -0.0009 0.0000 -0.0191 -0.0486 0.384 + 19 11.5760 2.6879 2.3787 0.3714 -0.0004 0.1683 0.1382 -0.0008 0.0000 -0.0190 -0.0476 0.387 + 20 12.4328 2.5181 2.1010 0.3383 0.0002 0.1636 0.1344 -0.0007 0.0000 -0.0189 -0.0466 0.391 + 21 13.2400 2.3582 1.8520 0.3085 0.0008 0.1593 0.1308 -0.0006 0.0000 -0.0187 -0.0457 0.393 + 22 13.9941 2.2087 1.6074 0.2808 0.0017 0.1549 0.1271 -0.0006 0.0000 -0.0185 -0.0447 0.396 + 23 14.6868 2.0715 1.3716 0.2544 0.0028 0.1496 0.1228 -0.0005 0.0000 -0.0182 -0.0434 0.398 + 24 15.3105 1.9479 1.1479 0.2282 0.0044 0.1427 0.1171 -0.0004 0.0000 -0.0176 -0.0417 0.400 + 25 15.8583 1.8393 0.9381 0.2005 0.0064 0.1328 0.1090 -0.0003 0.0000 -0.0168 -0.0391 0.404 + 26 16.3244 1.7470 0.7427 0.1697 0.0084 0.1183 0.0971 -0.0002 0.0000 -0.0157 -0.0355 0.412 + 27 16.6722 1.4928 0.4131 0.1369 0.0110 0.3062 0.0917 -0.0005 0.0000 -0.0133 -0.0169 0.395 + 28 16.9098 1.1466 0.2292 0.1036 0.0157 0.3014 0.0903 -0.0010 0.0000 -0.0092 -0.0149 0.352 + 29 17.0696 0.9138 0.1104 0.0653 0.0202 0.2386 0.0715 -0.0013 0.0000 -0.0037 -0.0101 0.301 + 30 17.1499 0.7967 0.0322 0.0224 0.0230 0.0940 0.0281 -0.0010 0.0000 -0.0004 -0.0035 0.265 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09194 Clsurf = 0.01467 - CYsurf = 0.00625 Cmsurf = -0.07352 - CDsurf = 0.00125 Cnsurf = -0.00069 - CDisurf = 0.00125 CDvsurf = 0.00000 + CLsurf = 0.09257 Clsurf = 0.01473 + CYsurf = 0.00625 Cmsurf = -0.07386 + CDsurf = 0.00122 Cnsurf = -0.00069 + CDisurf = 0.00122 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.17987 CDsurf = 0.00244 + CLsurf = 0.18109 CDsurf = 0.00238 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 1.6056 0.0485 0.2670 0.2071 0.0757 0.0000 -0.0106 0.0509 0.301 - 32 -0.1025 7.6885 1.0492 1.5557 0.0478 0.2609 0.2023 0.0168 0.0000 -0.0106 0.0499 0.303 - 33 -0.2837 7.5620 1.7073 1.5480 0.0461 0.2639 0.2047 0.0130 0.0000 -0.0099 0.0498 0.298 - 34 -0.5530 7.3741 2.3052 1.5357 0.0436 0.2685 0.2083 0.0114 0.0000 -0.0088 0.0496 0.292 - 35 -0.9075 7.1267 2.8223 1.5118 0.0404 0.2735 0.2121 0.0097 0.0000 -0.0077 0.0495 0.287 - 36 -1.3432 6.8226 3.2414 1.4715 0.0382 0.2781 0.2157 0.0083 0.0000 -0.0070 0.0496 0.282 - 37 -1.8554 6.4651 3.5491 1.4110 0.0401 0.2814 0.2182 0.0070 0.0000 -0.0066 0.0499 0.280 - 38 -2.4386 6.0582 3.7368 1.3260 0.0402 0.2822 0.2189 0.0046 0.0000 -0.0069 0.0502 0.282 - 39 -3.0862 5.6062 3.8005 1.2187 0.0314 0.2803 0.2174 0.0029 0.0000 -0.0080 0.0508 0.287 - 40 -3.7613 5.1351 3.4440 1.0970 0.0212 0.2755 0.2136 0.0009 0.0000 -0.0099 0.0516 0.297 - 41 -4.4532 4.6522 3.3149 0.9690 0.0114 0.2686 0.2083 -0.0006 0.0000 -0.0130 0.0530 0.312 - 42 -5.1831 4.1429 3.0930 0.8332 -0.0014 0.2593 0.2011 -0.0023 0.0000 -0.0172 0.0550 0.335 - 43 -6.0123 3.7903 3.4706 0.7117 -0.0084 0.2287 0.1878 -0.0028 0.0000 -0.0202 0.0596 0.357 - 44 -6.9353 3.6075 3.3775 0.6248 -0.0056 0.2109 0.1732 -0.0020 0.0000 -0.0207 0.0569 0.370 - 45 -7.8737 3.4215 3.2389 0.5555 -0.0036 0.1977 0.1624 -0.0015 0.0000 -0.0209 0.0546 0.378 - 46 -8.8172 3.2345 3.0619 0.4982 -0.0022 0.1876 0.1540 -0.0013 0.0000 -0.0208 0.0527 0.385 - 47 -9.7556 3.0486 2.8543 0.4496 -0.0014 0.1796 0.1475 -0.0011 0.0000 -0.0208 0.0512 0.391 - 48 -10.6786 2.8657 2.6240 0.4074 -0.0008 0.1732 0.1422 -0.0009 0.0000 -0.0207 0.0500 0.396 - 49 -11.5760 2.6879 2.3787 0.3704 -0.0003 0.1678 0.1378 -0.0008 0.0000 -0.0206 0.0489 0.400 - 50 -12.4328 2.5181 2.1010 0.3375 0.0002 0.1632 0.1340 -0.0007 0.0000 -0.0205 0.0480 0.403 - 51 -13.2400 2.3582 1.8520 0.3078 0.0009 0.1590 0.1305 -0.0006 0.0000 -0.0204 0.0471 0.406 - 52 -13.9941 2.2087 1.6074 0.2803 0.0017 0.1546 0.1269 -0.0006 0.0000 -0.0202 0.0461 0.409 - 53 -14.6868 2.0715 1.3716 0.2541 0.0029 0.1494 0.1227 -0.0005 0.0000 -0.0198 0.0449 0.412 - 54 -15.3105 1.9479 1.1479 0.2280 0.0044 0.1426 0.1171 -0.0004 0.0000 -0.0193 0.0431 0.415 - 55 -15.8583 1.8393 0.9381 0.2006 0.0064 0.1328 0.1090 -0.0003 0.0000 -0.0184 0.0406 0.419 - 56 -16.3244 1.7470 0.7427 0.1701 0.0087 0.1186 0.0974 -0.0002 0.0000 -0.0173 0.0370 0.428 - 57 -16.6722 1.4928 0.4131 0.1374 0.0113 0.3072 0.0920 -0.0005 0.0000 -0.0146 0.0176 0.408 - 58 -16.9098 1.1466 0.2292 0.1037 0.0158 0.3019 0.0904 -0.0010 0.0000 -0.0102 0.0153 0.363 - 59 -17.0696 0.9138 0.1104 0.0653 0.0200 0.2386 0.0715 -0.0013 0.0000 -0.0043 0.0104 0.310 - 60 -17.1499 0.7967 0.0322 0.0224 0.0223 0.0937 0.0281 -0.0011 0.0000 -0.0006 0.0036 0.271 + 31 -0.0114 7.7520 0.3539 1.6219 0.0484 0.2698 0.2092 0.0756 0.0000 -0.0120 0.0524 0.307 + 32 -0.1025 7.6885 1.0491 1.5712 0.0478 0.2635 0.2044 0.0168 0.0000 -0.0119 0.0513 0.308 + 33 -0.2837 7.5620 1.7073 1.5636 0.0465 0.2666 0.2068 0.0129 0.0000 -0.0112 0.0512 0.304 + 34 -0.5530 7.3741 2.3052 1.5514 0.0441 0.2712 0.2104 0.0111 0.0000 -0.0101 0.0511 0.298 + 35 -0.9075 7.1267 2.8223 1.5276 0.0410 0.2764 0.2144 0.0098 0.0000 -0.0091 0.0511 0.292 + 36 -1.3432 6.8226 3.2414 1.4868 0.0388 0.2810 0.2179 0.0081 0.0000 -0.0082 0.0511 0.288 + 37 -1.8554 6.4651 3.5491 1.4251 0.0407 0.2842 0.2204 0.0059 0.0000 -0.0078 0.0513 0.286 + 38 -2.4386 6.0582 3.7368 1.3403 0.0409 0.2852 0.2212 0.0048 0.0000 -0.0080 0.0516 0.286 + 39 -3.0862 5.6062 3.8005 1.2318 0.0323 0.2833 0.2197 0.0030 0.0000 -0.0088 0.0520 0.290 + 40 -3.7613 5.1351 3.4440 1.1075 0.0218 0.2781 0.2157 0.0013 0.0000 -0.0105 0.0525 0.299 + 41 -4.4532 4.6522 3.3149 0.9777 0.0114 0.2710 0.2102 -0.0007 0.0000 -0.0127 0.0532 0.311 + 42 -5.1831 4.1429 3.0930 0.8370 -0.0020 0.2605 0.2020 -0.0025 0.0000 -0.0162 0.0544 0.330 + 43 -6.0123 3.7903 3.4706 0.7143 -0.0089 0.2295 0.1885 -0.0028 0.0000 -0.0187 0.0585 0.349 + 44 -6.9353 3.6075 3.3775 0.6269 -0.0058 0.2116 0.1738 -0.0020 0.0000 -0.0192 0.0557 0.360 + 45 -7.8737 3.4215 3.2389 0.5573 -0.0037 0.1984 0.1629 -0.0015 0.0000 -0.0193 0.0533 0.368 + 46 -8.8172 3.2345 3.0619 0.4997 -0.0023 0.1882 0.1545 -0.0013 0.0000 -0.0192 0.0514 0.374 + 47 -9.7556 3.0486 2.8543 0.4509 -0.0014 0.1801 0.1479 -0.0011 0.0000 -0.0191 0.0499 0.379 + 48 -10.6786 2.8657 2.6239 0.4086 -0.0009 0.1736 0.1426 -0.0009 0.0000 -0.0191 0.0486 0.384 + 49 -11.5760 2.6879 2.3787 0.3714 -0.0004 0.1683 0.1382 -0.0008 0.0000 -0.0190 0.0476 0.387 + 50 -12.4328 2.5181 2.1010 0.3383 0.0002 0.1636 0.1344 -0.0007 0.0000 -0.0189 0.0466 0.391 + 51 -13.2400 2.3582 1.8520 0.3085 0.0008 0.1593 0.1308 -0.0006 0.0000 -0.0187 0.0457 0.393 + 52 -13.9941 2.2087 1.6074 0.2808 0.0017 0.1549 0.1271 -0.0006 0.0000 -0.0185 0.0447 0.396 + 53 -14.6868 2.0715 1.3716 0.2544 0.0028 0.1496 0.1228 -0.0005 0.0000 -0.0182 0.0434 0.398 + 54 -15.3105 1.9479 1.1479 0.2282 0.0044 0.1427 0.1171 -0.0004 0.0000 -0.0176 0.0417 0.400 + 55 -15.8583 1.8393 0.9381 0.2005 0.0064 0.1328 0.1090 -0.0003 0.0000 -0.0168 0.0391 0.404 + 56 -16.3244 1.7470 0.7427 0.1697 0.0084 0.1183 0.0971 -0.0002 0.0000 -0.0157 0.0355 0.412 + 57 -16.6722 1.4928 0.4131 0.1369 0.0110 0.3062 0.0917 -0.0005 0.0000 -0.0133 0.0169 0.395 + 58 -16.9098 1.1466 0.2292 0.1036 0.0157 0.3014 0.0903 -0.0010 0.0000 -0.0092 0.0149 0.352 + 59 -17.0696 0.9138 0.1104 0.0653 0.0202 0.2386 0.0715 -0.0013 0.0000 -0.0037 0.0101 0.301 + 60 -17.1499 0.7967 0.0322 0.0224 0.0230 0.0940 0.0281 -0.0010 0.0000 -0.0004 0.0035 0.265 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01272 Clsurf = 0.00116 - CYsurf = 0.00204 Cmsurf = 0.06077 - CDsurf = -0.00018 Cnsurf = -0.00122 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01286 Clsurf = 0.00117 + CYsurf = 0.00207 Cmsurf = 0.06142 + CDsurf = -0.00018 Cnsurf = -0.00123 CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.07754 CDsurf = -0.00109 + CLsurf = -0.07838 CDsurf = -0.00111 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.3111 0.0110 -0.0940 -0.0728 0.0128 0.0000 0.0034 0.0183 0.297 - 62 0.0418 4.2566 0.2392 -0.3308 0.0108 -0.1002 -0.0777 0.0003 0.0000 0.0033 0.0192 0.292 - 63 0.1156 4.2274 0.3930 -0.3323 0.0105 -0.1014 -0.0786 -0.0005 0.0000 0.0030 0.0191 0.288 - 64 0.2254 4.1839 0.5386 -0.3326 0.0101 -0.1025 -0.0795 -0.0008 0.0000 0.0026 0.0190 0.283 - 65 0.3698 4.1268 0.6730 -0.3324 0.0099 -0.1039 -0.0805 -0.0009 0.0000 0.0021 0.0187 0.276 - 66 0.5474 4.0565 0.7936 -0.3315 0.0096 -0.1054 -0.0817 -0.0010 0.0000 0.0015 0.0185 0.269 - 67 0.7617 3.9717 0.9441 -0.3299 0.0095 -0.1071 -0.0831 -0.0011 0.0000 0.0010 0.0183 0.262 - 68 1.0116 3.8728 1.0344 -0.3268 0.0095 -0.1089 -0.0844 -0.0013 0.0000 0.0005 0.0182 0.256 - 69 1.2891 3.7630 1.1046 -0.3223 0.0098 -0.1105 -0.0857 -0.0013 0.0000 0.0001 0.0181 0.251 - 70 1.5912 3.6435 1.1542 -0.3157 0.0103 -0.1118 -0.0866 -0.0014 0.0000 -0.0003 0.0181 0.247 - 71 1.9146 3.5155 1.1831 -0.3069 0.0108 -0.1126 -0.0873 -0.0015 0.0000 -0.0005 0.0180 0.244 - 72 2.2558 3.3805 1.1921 -0.2959 0.0110 -0.1129 -0.0875 -0.0015 0.0000 -0.0007 0.0179 0.242 - 73 2.6109 3.2400 1.1821 -0.2826 0.0109 -0.1125 -0.0872 -0.0015 0.0000 -0.0008 0.0177 0.240 - 74 2.9762 3.0955 1.1548 -0.2672 0.0104 -0.1113 -0.0863 -0.0015 0.0000 -0.0009 0.0174 0.239 - 75 3.3476 2.9485 1.1122 -0.2501 0.0097 -0.1094 -0.0848 -0.0014 0.0000 -0.0010 0.0171 0.239 - 76 3.7210 2.8008 1.0564 -0.2317 0.0090 -0.1067 -0.0827 -0.0014 0.0000 -0.0009 0.0167 0.239 - 77 4.0924 2.6538 0.9900 -0.2126 0.0082 -0.1034 -0.0801 -0.0013 0.0000 -0.0009 0.0161 0.238 - 78 4.4577 2.5093 0.9155 -0.1934 0.0075 -0.0994 -0.0771 -0.0012 0.0000 -0.0009 0.0155 0.238 - 79 4.8128 2.3687 0.8353 -0.1745 0.0068 -0.0950 -0.0737 -0.0011 0.0000 -0.0009 0.0148 0.238 - 80 5.1540 2.2338 0.7518 -0.1563 0.0062 -0.0902 -0.0700 -0.0010 0.0000 -0.0009 0.0140 0.237 - 81 5.4774 2.1058 0.6671 -0.1390 0.0056 -0.0851 -0.0660 -0.0009 0.0000 -0.0010 0.0131 0.235 - 82 5.7795 1.9862 0.5830 -0.1227 0.0050 -0.0797 -0.0618 -0.0008 0.0000 -0.0011 0.0121 0.231 - 83 6.0570 1.8764 0.5012 -0.1074 0.0044 -0.0738 -0.0572 -0.0007 0.0000 -0.0013 0.0109 0.227 - 84 6.3069 1.7776 0.4225 -0.0930 0.0038 -0.0675 -0.0523 -0.0006 0.0000 -0.0016 0.0097 0.219 - 85 6.5264 1.6907 0.3478 -0.0792 0.0032 -0.0605 -0.0469 -0.0005 0.0000 -0.0019 0.0083 0.210 - 86 6.7314 1.6096 0.3326 -0.0653 0.0027 -0.0523 -0.0406 -0.0005 0.0000 -0.0022 0.0067 0.197 - 87 6.9144 1.5372 0.2507 -0.0507 0.0022 -0.0425 -0.0330 -0.0004 0.0000 -0.0023 0.0050 0.180 - 88 7.0535 1.4822 0.1746 -0.0362 0.0018 -0.0315 -0.0244 -0.0003 0.0000 -0.0022 0.0033 0.161 - 89 7.1471 1.4451 0.1029 -0.0217 0.0015 -0.0194 -0.0150 -0.0002 0.0000 -0.0016 0.0018 0.145 - 90 7.1941 1.4265 0.0340 -0.0072 0.0014 -0.0065 -0.0051 -0.0001 0.0000 -0.0006 0.0006 0.135 + 61 0.0047 4.2713 0.0803 -0.3146 0.0111 -0.0950 -0.0737 0.0131 0.0000 0.0035 0.0185 0.297 + 62 0.0418 4.2566 0.2392 -0.3348 0.0109 -0.1015 -0.0787 0.0003 0.0000 0.0033 0.0194 0.292 + 63 0.1156 4.2274 0.3930 -0.3363 0.0105 -0.1026 -0.0796 -0.0005 0.0000 0.0031 0.0194 0.288 + 64 0.2254 4.1839 0.5386 -0.3367 0.0102 -0.1038 -0.0805 -0.0008 0.0000 0.0026 0.0192 0.283 + 65 0.3698 4.1268 0.6730 -0.3364 0.0100 -0.1051 -0.0815 -0.0009 0.0000 0.0021 0.0190 0.276 + 66 0.5474 4.0565 0.7936 -0.3356 0.0097 -0.1067 -0.0827 -0.0010 0.0000 0.0015 0.0187 0.268 + 67 0.7617 3.9717 0.9441 -0.3339 0.0096 -0.1084 -0.0841 -0.0012 0.0000 0.0010 0.0186 0.262 + 68 1.0116 3.8728 1.0344 -0.3309 0.0096 -0.1102 -0.0854 -0.0013 0.0000 0.0005 0.0184 0.256 + 69 1.2891 3.7630 1.1046 -0.3262 0.0099 -0.1118 -0.0867 -0.0014 0.0000 0.0001 0.0183 0.251 + 70 1.5912 3.6435 1.1542 -0.3195 0.0104 -0.1131 -0.0877 -0.0015 0.0000 -0.0003 0.0183 0.247 + 71 1.9146 3.5155 1.1831 -0.3106 0.0109 -0.1140 -0.0884 -0.0015 0.0000 -0.0005 0.0182 0.244 + 72 2.2558 3.3805 1.1921 -0.2994 0.0111 -0.1143 -0.0886 -0.0015 0.0000 -0.0007 0.0181 0.242 + 73 2.6109 3.2400 1.1821 -0.2859 0.0110 -0.1138 -0.0882 -0.0015 0.0000 -0.0009 0.0179 0.240 + 74 2.9762 3.0955 1.1548 -0.2702 0.0105 -0.1126 -0.0873 -0.0015 0.0000 -0.0009 0.0176 0.239 + 75 3.3476 2.9485 1.1122 -0.2528 0.0098 -0.1106 -0.0857 -0.0015 0.0000 -0.0010 0.0173 0.239 + 76 3.7210 2.8008 1.0564 -0.2342 0.0091 -0.1078 -0.0836 -0.0014 0.0000 -0.0010 0.0168 0.238 + 77 4.0924 2.6538 0.9900 -0.2148 0.0083 -0.1044 -0.0809 -0.0013 0.0000 -0.0009 0.0163 0.238 + 78 4.4577 2.5093 0.9155 -0.1953 0.0076 -0.1004 -0.0778 -0.0012 0.0000 -0.0009 0.0156 0.238 + 79 4.8128 2.3687 0.8353 -0.1761 0.0069 -0.0959 -0.0743 -0.0011 0.0000 -0.0009 0.0149 0.238 + 80 5.1540 2.2338 0.7518 -0.1576 0.0063 -0.0910 -0.0706 -0.0010 0.0000 -0.0009 0.0141 0.237 + 81 5.4774 2.1058 0.6671 -0.1401 0.0057 -0.0858 -0.0665 -0.0009 0.0000 -0.0010 0.0132 0.235 + 82 5.7795 1.9862 0.5830 -0.1236 0.0051 -0.0803 -0.0622 -0.0008 0.0000 -0.0011 0.0122 0.232 + 83 6.0570 1.8764 0.5012 -0.1081 0.0044 -0.0743 -0.0576 -0.0007 0.0000 -0.0013 0.0110 0.227 + 84 6.3069 1.7776 0.4225 -0.0936 0.0038 -0.0679 -0.0527 -0.0006 0.0000 -0.0016 0.0098 0.220 + 85 6.5264 1.6907 0.3478 -0.0797 0.0033 -0.0608 -0.0472 -0.0005 0.0000 -0.0019 0.0084 0.210 + 86 6.7314 1.6096 0.3326 -0.0657 0.0027 -0.0526 -0.0408 -0.0005 0.0000 -0.0022 0.0068 0.197 + 87 6.9144 1.5372 0.2507 -0.0510 0.0022 -0.0428 -0.0332 -0.0004 0.0000 -0.0023 0.0050 0.180 + 88 7.0535 1.4822 0.1746 -0.0363 0.0018 -0.0316 -0.0245 -0.0003 0.0000 -0.0022 0.0033 0.161 + 89 7.1471 1.4451 0.1029 -0.0218 0.0015 -0.0195 -0.0151 -0.0002 0.0000 -0.0016 0.0018 0.145 + 90 7.1941 1.4265 0.0340 -0.0073 0.0014 -0.0066 -0.0051 -0.0001 0.0000 -0.0006 0.0006 0.135 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01272 Clsurf = -0.00116 - CYsurf = -0.00204 Cmsurf = 0.06077 - CDsurf = -0.00018 Cnsurf = 0.00122 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01286 Clsurf = -0.00117 + CYsurf = -0.00207 Cmsurf = 0.06142 + CDsurf = -0.00018 Cnsurf = 0.00123 CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.07754 CDsurf = -0.00109 + CLsurf = -0.07838 CDsurf = -0.00111 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.3111 0.0110 -0.0940 -0.0728 0.0128 0.0000 0.0034 -0.0183 0.297 - 92 -0.0418 4.2566 0.2392 -0.3308 0.0108 -0.1002 -0.0777 0.0003 0.0000 0.0033 -0.0192 0.292 - 93 -0.1156 4.2274 0.3930 -0.3323 0.0105 -0.1014 -0.0786 -0.0005 0.0000 0.0030 -0.0191 0.288 - 94 -0.2254 4.1839 0.5386 -0.3326 0.0101 -0.1025 -0.0795 -0.0008 0.0000 0.0026 -0.0190 0.283 - 95 -0.3698 4.1268 0.6730 -0.3324 0.0099 -0.1039 -0.0805 -0.0009 0.0000 0.0021 -0.0187 0.276 - 96 -0.5474 4.0565 0.7936 -0.3315 0.0096 -0.1054 -0.0817 -0.0010 0.0000 0.0015 -0.0185 0.269 - 97 -0.7617 3.9717 0.9441 -0.3299 0.0095 -0.1071 -0.0831 -0.0011 0.0000 0.0010 -0.0183 0.262 - 98 -1.0116 3.8728 1.0344 -0.3268 0.0095 -0.1089 -0.0844 -0.0013 0.0000 0.0005 -0.0182 0.256 - 99 -1.2891 3.7630 1.1046 -0.3223 0.0098 -0.1105 -0.0857 -0.0013 0.0000 0.0001 -0.0181 0.251 - 100 -1.5912 3.6435 1.1542 -0.3157 0.0103 -0.1118 -0.0866 -0.0014 0.0000 -0.0003 -0.0181 0.247 - 101 -1.9146 3.5155 1.1831 -0.3069 0.0108 -0.1126 -0.0873 -0.0015 0.0000 -0.0005 -0.0180 0.244 - 102 -2.2558 3.3805 1.1921 -0.2959 0.0110 -0.1129 -0.0875 -0.0015 0.0000 -0.0007 -0.0179 0.242 - 103 -2.6109 3.2400 1.1821 -0.2825 0.0109 -0.1125 -0.0872 -0.0015 0.0000 -0.0008 -0.0177 0.240 - 104 -2.9762 3.0955 1.1548 -0.2672 0.0104 -0.1113 -0.0863 -0.0015 0.0000 -0.0009 -0.0174 0.239 - 105 -3.3476 2.9485 1.1122 -0.2501 0.0097 -0.1094 -0.0848 -0.0014 0.0000 -0.0010 -0.0171 0.239 - 106 -3.7210 2.8008 1.0564 -0.2317 0.0090 -0.1067 -0.0827 -0.0014 0.0000 -0.0009 -0.0167 0.239 - 107 -4.0924 2.6538 0.9900 -0.2126 0.0082 -0.1034 -0.0801 -0.0013 0.0000 -0.0009 -0.0161 0.238 - 108 -4.4577 2.5093 0.9155 -0.1934 0.0075 -0.0994 -0.0771 -0.0012 0.0000 -0.0009 -0.0155 0.238 - 109 -4.8128 2.3687 0.8353 -0.1745 0.0068 -0.0950 -0.0737 -0.0011 0.0000 -0.0009 -0.0148 0.238 - 110 -5.1540 2.2338 0.7518 -0.1563 0.0062 -0.0902 -0.0700 -0.0010 0.0000 -0.0009 -0.0140 0.237 - 111 -5.4774 2.1058 0.6671 -0.1390 0.0056 -0.0851 -0.0660 -0.0009 0.0000 -0.0010 -0.0131 0.235 - 112 -5.7795 1.9862 0.5830 -0.1227 0.0050 -0.0797 -0.0618 -0.0008 0.0000 -0.0011 -0.0121 0.231 - 113 -6.0570 1.8764 0.5012 -0.1074 0.0044 -0.0738 -0.0572 -0.0007 0.0000 -0.0013 -0.0109 0.227 - 114 -6.3069 1.7776 0.4225 -0.0930 0.0038 -0.0675 -0.0523 -0.0006 0.0000 -0.0016 -0.0097 0.219 - 115 -6.5264 1.6907 0.3478 -0.0792 0.0032 -0.0605 -0.0469 -0.0005 0.0000 -0.0019 -0.0083 0.210 - 116 -6.7314 1.6096 0.3326 -0.0653 0.0027 -0.0523 -0.0406 -0.0005 0.0000 -0.0022 -0.0067 0.197 - 117 -6.9144 1.5372 0.2507 -0.0507 0.0022 -0.0425 -0.0330 -0.0004 0.0000 -0.0023 -0.0050 0.180 - 118 -7.0535 1.4822 0.1746 -0.0362 0.0018 -0.0315 -0.0244 -0.0003 0.0000 -0.0022 -0.0033 0.161 - 119 -7.1471 1.4451 0.1029 -0.0217 0.0015 -0.0194 -0.0150 -0.0002 0.0000 -0.0016 -0.0018 0.145 - 120 -7.1941 1.4265 0.0340 -0.0072 0.0014 -0.0065 -0.0051 -0.0001 0.0000 -0.0006 -0.0006 0.135 + 91 -0.0047 4.2713 0.0803 -0.3146 0.0111 -0.0950 -0.0737 0.0131 0.0000 0.0035 -0.0185 0.297 + 92 -0.0418 4.2566 0.2392 -0.3348 0.0109 -0.1015 -0.0787 0.0003 0.0000 0.0033 -0.0194 0.292 + 93 -0.1156 4.2274 0.3930 -0.3363 0.0105 -0.1026 -0.0796 -0.0005 0.0000 0.0031 -0.0194 0.288 + 94 -0.2254 4.1839 0.5386 -0.3367 0.0102 -0.1038 -0.0805 -0.0008 0.0000 0.0026 -0.0192 0.283 + 95 -0.3698 4.1268 0.6730 -0.3364 0.0100 -0.1051 -0.0815 -0.0009 0.0000 0.0021 -0.0190 0.276 + 96 -0.5474 4.0565 0.7936 -0.3356 0.0097 -0.1067 -0.0827 -0.0010 0.0000 0.0015 -0.0187 0.268 + 97 -0.7617 3.9717 0.9441 -0.3339 0.0096 -0.1084 -0.0841 -0.0012 0.0000 0.0010 -0.0186 0.262 + 98 -1.0116 3.8728 1.0344 -0.3309 0.0096 -0.1102 -0.0854 -0.0013 0.0000 0.0005 -0.0184 0.256 + 99 -1.2891 3.7630 1.1046 -0.3262 0.0099 -0.1118 -0.0867 -0.0014 0.0000 0.0001 -0.0183 0.251 + 100 -1.5912 3.6435 1.1542 -0.3195 0.0104 -0.1131 -0.0877 -0.0015 0.0000 -0.0003 -0.0183 0.247 + 101 -1.9146 3.5155 1.1831 -0.3106 0.0109 -0.1140 -0.0884 -0.0015 0.0000 -0.0005 -0.0182 0.244 + 102 -2.2558 3.3805 1.1921 -0.2994 0.0111 -0.1143 -0.0886 -0.0015 0.0000 -0.0007 -0.0181 0.242 + 103 -2.6109 3.2400 1.1821 -0.2859 0.0110 -0.1138 -0.0882 -0.0015 0.0000 -0.0009 -0.0179 0.240 + 104 -2.9762 3.0955 1.1548 -0.2702 0.0105 -0.1126 -0.0873 -0.0015 0.0000 -0.0009 -0.0176 0.239 + 105 -3.3476 2.9485 1.1122 -0.2528 0.0098 -0.1106 -0.0857 -0.0015 0.0000 -0.0010 -0.0173 0.239 + 106 -3.7210 2.8008 1.0564 -0.2342 0.0091 -0.1078 -0.0836 -0.0014 0.0000 -0.0010 -0.0168 0.238 + 107 -4.0924 2.6538 0.9900 -0.2148 0.0083 -0.1044 -0.0809 -0.0013 0.0000 -0.0009 -0.0163 0.238 + 108 -4.4577 2.5093 0.9155 -0.1953 0.0076 -0.1004 -0.0778 -0.0012 0.0000 -0.0009 -0.0156 0.238 + 109 -4.8128 2.3687 0.8353 -0.1761 0.0069 -0.0959 -0.0743 -0.0011 0.0000 -0.0009 -0.0149 0.238 + 110 -5.1540 2.2338 0.7518 -0.1576 0.0063 -0.0910 -0.0706 -0.0010 0.0000 -0.0009 -0.0141 0.237 + 111 -5.4774 2.1058 0.6671 -0.1401 0.0057 -0.0858 -0.0665 -0.0009 0.0000 -0.0010 -0.0132 0.235 + 112 -5.7795 1.9862 0.5830 -0.1236 0.0051 -0.0803 -0.0622 -0.0008 0.0000 -0.0011 -0.0122 0.232 + 113 -6.0570 1.8764 0.5012 -0.1081 0.0044 -0.0743 -0.0576 -0.0007 0.0000 -0.0013 -0.0110 0.227 + 114 -6.3069 1.7776 0.4225 -0.0936 0.0038 -0.0679 -0.0527 -0.0006 0.0000 -0.0016 -0.0098 0.220 + 115 -6.5264 1.6907 0.3478 -0.0797 0.0033 -0.0608 -0.0472 -0.0005 0.0000 -0.0019 -0.0084 0.210 + 116 -6.7314 1.6096 0.3326 -0.0657 0.0027 -0.0526 -0.0408 -0.0005 0.0000 -0.0022 -0.0068 0.197 + 117 -6.9144 1.5372 0.2507 -0.0510 0.0022 -0.0428 -0.0332 -0.0004 0.0000 -0.0023 -0.0050 0.180 + 118 -7.0535 1.4822 0.1746 -0.0363 0.0018 -0.0316 -0.0245 -0.0003 0.0000 -0.0022 -0.0033 0.161 + 119 -7.1471 1.4451 0.1029 -0.0218 0.0015 -0.0195 -0.0151 -0.0002 0.0000 -0.0016 -0.0018 0.145 + 120 -7.1941 1.4265 0.0340 -0.0073 0.0014 -0.0066 -0.0051 -0.0001 0.0000 -0.0006 -0.0006 0.135 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 - CLsurf = 0.00000 Clsurf = -0.00000 - CYsurf = -0.00000 Cmsurf = -0.00000 - CDsurf = -0.00000 Cnsurf = 0.00000 + Surface area = 34.910358 Ave. chord = 4.190919 + CLsurf = 0.00000 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.705 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.808 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.975 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.755 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.620 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.569 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.652 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.731 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.905 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 139 0.0000 2.6103 0.9908 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.488 - 140 0.0000 2.3983 0.8670 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.161 - 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.004 - 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.026 - 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.071 - 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.092 - 145 0.0000 1.5493 0.3400 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.096 - 146 0.0000 1.4342 0.2622 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.096 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.060 - 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.044 - 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.028 - 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.034 + 125 0.0000 8.6377 2.0517 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 126 0.0000 8.0598 2.2181 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 127 0.0000 7.4000 2.2957 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 128 0.0000 6.6646 2.2808 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 129 0.0000 5.8609 2.1733 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 130 0.0000 4.9969 1.9773 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 131 0.0000 4.4389 1.6667 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 132 0.0000 4.2198 1.6478 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 133 0.0000 3.9932 1.6033 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 134 0.0000 3.7615 1.5362 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.844 + 135 0.0000 3.5271 1.4499 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.475 + 136 0.0000 3.2923 1.3482 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.254 + 137 0.0000 3.0597 1.2352 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.091 + 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.023 + 139 0.0000 2.6103 0.9908 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.082 + 140 0.0000 2.3983 0.8670 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.097 + 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.157 + 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.179 + 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.183 + 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.184 + 145 0.0000 1.5493 0.3400 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.162 + 146 0.0000 1.4342 0.2622 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.140 + 147 0.0000 1.3407 0.1933 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.126 + 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.094 + 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.094 + 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.080 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00508 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = -0.00374 - CDsurf = 0.00002 Cnsurf = -0.00000 + CLsurf = -0.00514 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00367 + CDsurf = 0.00002 Cnsurf = 0.00000 CDisurf = 0.00002 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00512 CDsurf = 0.00002 + CLsurf = -0.00519 CDsurf = 0.00002 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.1330 -0.0065 -0.0631 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.409 - 152 -1.3090 31.2096 11.6724 -0.1736 -0.0002 -0.0217 -0.0056 0.0000 0.0000 0.0007 0.0005 0.372 - 153 -0.9350 34.0626 12.7394 -0.1807 0.0138 -0.0130 -0.0053 0.0000 0.0000 0.0003 0.0005 0.308 - 154 -0.5610 36.1619 13.5246 -0.1805 0.0217 -0.0084 -0.0050 0.0001 0.0000 0.0001 0.0006 0.262 - 155 -0.1870 37.5332 14.0374 -0.1795 0.0252 -0.0056 -0.0048 0.0001 0.0000 -0.0001 0.0008 0.239 - 156 0.1870 37.5332 14.0374 -0.1795 0.0252 -0.0056 -0.0048 0.0001 0.0000 -0.0001 0.0008 0.239 - 157 0.5610 36.1619 13.5246 -0.1805 0.0217 -0.0084 -0.0050 0.0001 0.0000 0.0001 0.0006 0.262 - 158 0.9350 34.0626 12.7394 -0.1807 0.0138 -0.0130 -0.0053 0.0000 0.0000 0.0003 0.0005 0.308 - 159 1.3090 31.2096 11.6724 -0.1736 -0.0002 -0.0217 -0.0056 0.0000 0.0000 0.0007 0.0005 0.372 - 160 1.6830 26.5957 9.9468 -0.1330 -0.0065 -0.0631 -0.0050 -0.0001 0.0000 0.0008 0.0003 0.409 + 151 -1.6830 26.5957 9.9468 -0.1348 -0.0065 -0.0639 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.412 + 152 -1.3090 31.2096 11.6724 -0.1759 -0.0001 -0.0220 -0.0056 0.0000 0.0000 0.0007 0.0005 0.374 + 153 -0.9350 34.0626 12.7394 -0.1831 0.0139 -0.0131 -0.0054 0.0000 0.0000 0.0003 0.0006 0.311 + 154 -0.5610 36.1619 13.5246 -0.1829 0.0219 -0.0085 -0.0051 0.0001 0.0000 0.0001 0.0006 0.265 + 155 -0.1870 37.5332 14.0374 -0.1820 0.0255 -0.0056 -0.0048 0.0001 0.0000 -0.0000 0.0008 0.242 + 156 0.1870 37.5332 14.0374 -0.1820 0.0255 -0.0056 -0.0048 0.0001 0.0000 -0.0000 0.0008 0.242 + 157 0.5610 36.1619 13.5246 -0.1829 0.0219 -0.0085 -0.0051 0.0001 0.0000 0.0001 0.0006 0.265 + 158 0.9350 34.0626 12.7394 -0.1831 0.0139 -0.0131 -0.0054 0.0000 0.0000 0.0003 0.0006 0.311 + 159 1.3090 31.2096 11.6724 -0.1759 -0.0001 -0.0220 -0.0056 0.0000 0.0000 0.0007 0.0005 0.374 + 160 1.6830 26.5957 9.9468 -0.1348 -0.0065 -0.0639 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.412 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = -0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = -0.00000 Cnsurf = -0.00000 - CDisurf = -0.00000 CDvsurf = 0.00000 + CDsurf = 0.00000 Cnsurf = -0.00000 + CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = 0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.979 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.717 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.686 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.669 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.663 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.650 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.629 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.585 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.522 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.490 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 1.172 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.666 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.660 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.645 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.649 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.630 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.611 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.562 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.503 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.451 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_03_03.txt b/regression/scripts/AVL/avl_files/strip_forces_case_03_03.txt index 064291d1c5..c77114444d 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_03_03.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_03_03.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.17498 Clsurf = -0.03188 - CYsurf = -0.01167 Cmsurf = -0.15087 - CDsurf = 0.00322 Cnsurf = 0.00019 - CDisurf = 0.00322 CDvsurf = 0.00000 + CLsurf = 0.17562 Clsurf = -0.03194 + CYsurf = -0.01162 Cmsurf = -0.15120 + CDsurf = 0.00313 Cnsurf = 0.00019 + CDisurf = 0.00313 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.34231 CDsurf = 0.00629 + CLsurf = 0.34354 CDsurf = 0.00610 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 2.5218 0.0846 0.4123 0.3194 0.1754 0.0000 -0.0169 -0.0802 0.303 - 2 0.1025 7.6885 1.0492 2.4045 0.0839 0.4023 0.3116 0.0369 0.0000 -0.0170 -0.0777 0.304 - 3 0.2837 7.5620 1.7073 2.3915 0.0824 0.4073 0.3155 0.0280 0.0000 -0.0158 -0.0775 0.300 - 4 0.5530 7.3741 2.3052 2.3773 0.0797 0.4153 0.3217 0.0248 0.0000 -0.0140 -0.0773 0.293 - 5 0.9075 7.1267 2.8223 2.3503 0.0757 0.4250 0.3292 0.0216 0.0000 -0.0121 -0.0772 0.287 - 6 1.3432 6.8226 3.2414 2.3053 0.0705 0.4356 0.3374 0.0190 0.0000 -0.0105 -0.0776 0.281 - 7 1.8554 6.4651 3.5491 2.2380 0.0646 0.4464 0.3458 0.0165 0.0000 -0.0095 -0.0785 0.277 - 8 2.4386 6.0582 3.7368 2.1408 0.0574 0.4559 0.3532 0.0118 0.0000 -0.0093 -0.0798 0.276 - 9 3.0862 5.6062 3.8005 2.0185 0.0472 0.4647 0.3600 0.0088 0.0000 -0.0099 -0.0816 0.277 - 10 3.7613 5.1351 3.4440 1.8771 0.0365 0.4720 0.3656 0.0045 0.0000 -0.0116 -0.0842 0.282 - 11 4.4532 4.6522 3.3149 1.7265 0.0255 0.4794 0.3713 0.0013 0.0000 -0.0145 -0.0876 0.289 - 12 5.1831 4.1429 3.0930 1.5630 0.0102 0.4875 0.3776 -0.0029 0.0000 -0.0182 -0.0919 0.298 - 13 6.0123 3.7903 3.4706 1.4116 0.0010 0.4553 0.3728 -0.0045 0.0000 -0.0201 -0.1010 0.304 - 14 6.9353 3.6075 3.3775 1.2980 0.0025 0.4399 0.3602 -0.0031 0.0000 -0.0206 -0.0986 0.307 - 15 7.8737 3.4215 3.2389 1.2018 0.0029 0.4294 0.3515 -0.0025 0.0000 -0.0206 -0.0968 0.309 - 16 8.8172 3.2345 3.0619 1.1166 0.0033 0.4220 0.3455 -0.0022 0.0000 -0.0206 -0.0954 0.310 - 17 9.7556 3.0486 2.8543 1.0388 0.0037 0.4165 0.3410 -0.0020 0.0000 -0.0205 -0.0943 0.310 - 18 10.6786 2.8657 2.6240 0.9666 0.0044 0.4123 0.3376 -0.0018 0.0000 -0.0203 -0.0934 0.310 - 19 11.5760 2.6879 2.3787 0.8988 0.0053 0.4087 0.3346 -0.0017 0.0000 -0.0202 -0.0926 0.310 - 20 12.4328 2.5181 2.1010 0.8345 0.0064 0.4051 0.3317 -0.0017 0.0000 -0.0199 -0.0917 0.310 - 21 13.2400 2.3582 1.8520 0.7728 0.0079 0.4006 0.3280 -0.0016 0.0000 -0.0196 -0.0905 0.310 - 22 13.9941 2.2087 1.6074 0.7121 0.0099 0.3941 0.3227 -0.0015 0.0000 -0.0190 -0.0888 0.309 - 23 14.6868 2.0715 1.3716 0.6509 0.0128 0.3841 0.3145 -0.0014 0.0000 -0.0181 -0.0862 0.307 - 24 15.3105 1.9479 1.1479 0.5865 0.0165 0.3680 0.3013 -0.0012 0.0000 -0.0167 -0.0820 0.305 - 25 15.8583 1.8393 0.9381 0.5156 0.0208 0.3426 0.2805 -0.0008 0.0000 -0.0150 -0.0759 0.304 - 26 16.3244 1.7470 0.7427 0.4351 0.0254 0.3044 0.2492 0.0001 0.0000 -0.0147 -0.0686 0.309 - 27 16.6722 1.4928 0.4131 0.3482 0.0304 0.7852 0.2335 -0.0031 0.0000 -0.0134 -0.0340 0.307 - 28 16.9098 1.1466 0.2292 0.2593 0.0379 0.7618 0.2266 -0.0071 0.0000 -0.0037 -0.0287 0.266 - 29 17.0696 0.9138 0.1104 0.1611 0.0445 0.5945 0.1768 -0.0101 0.0000 0.0069 -0.0178 0.211 - 30 17.1499 0.7967 0.0322 0.0547 0.0479 0.2320 0.0690 -0.0070 0.0000 0.0062 -0.0053 0.160 + 1 0.0114 7.7520 0.3539 2.5385 0.0845 0.4151 0.3215 0.1755 0.0000 -0.0183 -0.0818 0.307 + 2 0.1025 7.6885 1.0491 2.4201 0.0840 0.4049 0.3137 0.0368 0.0000 -0.0183 -0.0792 0.308 + 3 0.2837 7.5620 1.7073 2.4071 0.0827 0.4099 0.3175 0.0279 0.0000 -0.0171 -0.0790 0.304 + 4 0.5530 7.3741 2.3052 2.3925 0.0802 0.4180 0.3238 0.0241 0.0000 -0.0153 -0.0788 0.297 + 5 0.9075 7.1267 2.8223 2.3660 0.0763 0.4279 0.3314 0.0217 0.0000 -0.0134 -0.0788 0.290 + 6 1.3432 6.8226 3.2414 2.3202 0.0711 0.4385 0.3396 0.0183 0.0000 -0.0118 -0.0791 0.285 + 7 1.8554 6.4651 3.5491 2.2508 0.0652 0.4491 0.3479 0.0139 0.0000 -0.0107 -0.0799 0.281 + 8 2.4386 6.0582 3.7368 2.1552 0.0581 0.4590 0.3555 0.0121 0.0000 -0.0103 -0.0811 0.279 + 9 3.0862 5.6062 3.8005 2.0316 0.0481 0.4677 0.3623 0.0087 0.0000 -0.0108 -0.0828 0.280 + 10 3.7613 5.1351 3.4440 1.8867 0.0371 0.4744 0.3675 0.0055 0.0000 -0.0122 -0.0850 0.283 + 11 4.4532 4.6522 3.3149 1.7374 0.0254 0.4824 0.3737 0.0010 0.0000 -0.0141 -0.0878 0.288 + 12 5.1831 4.1429 3.0930 1.5668 0.0096 0.4887 0.3785 -0.0033 0.0000 -0.0172 -0.0913 0.296 + 13 6.0123 3.7903 3.4706 1.4142 0.0005 0.4562 0.3735 -0.0045 0.0000 -0.0187 -0.0999 0.300 + 14 6.9353 3.6075 3.3775 1.3001 0.0023 0.4406 0.3607 -0.0031 0.0000 -0.0190 -0.0974 0.303 + 15 7.8737 3.4215 3.2389 1.2035 0.0028 0.4300 0.3521 -0.0025 0.0000 -0.0191 -0.0955 0.304 + 16 8.8172 3.2345 3.0619 1.1181 0.0031 0.4226 0.3460 -0.0022 0.0000 -0.0190 -0.0940 0.305 + 17 9.7556 3.0486 2.8543 1.0401 0.0037 0.4170 0.3414 -0.0020 0.0000 -0.0188 -0.0929 0.305 + 18 10.6786 2.8657 2.6239 0.9677 0.0044 0.4128 0.3380 -0.0019 0.0000 -0.0187 -0.0920 0.305 + 19 11.5760 2.6879 2.3787 0.8997 0.0052 0.4092 0.3350 -0.0018 0.0000 -0.0185 -0.0912 0.305 + 20 12.4328 2.5181 2.1010 0.8353 0.0063 0.4055 0.3320 -0.0017 0.0000 -0.0183 -0.0903 0.305 + 21 13.2400 2.3582 1.8520 0.7734 0.0078 0.4009 0.3282 -0.0016 0.0000 -0.0179 -0.0891 0.305 + 22 13.9941 2.2087 1.6074 0.7126 0.0099 0.3944 0.3229 -0.0015 0.0000 -0.0173 -0.0874 0.304 + 23 14.6868 2.0715 1.3716 0.6512 0.0128 0.3843 0.3146 -0.0014 0.0000 -0.0164 -0.0848 0.302 + 24 15.3105 1.9479 1.1479 0.5867 0.0164 0.3681 0.3014 -0.0012 0.0000 -0.0150 -0.0806 0.300 + 25 15.8583 1.8393 0.9381 0.5155 0.0207 0.3426 0.2805 -0.0008 0.0000 -0.0134 -0.0745 0.298 + 26 16.3244 1.7470 0.7427 0.4347 0.0251 0.3041 0.2490 0.0001 0.0000 -0.0130 -0.0671 0.302 + 27 16.6722 1.4928 0.4131 0.3477 0.0301 0.7842 0.2332 -0.0032 0.0000 -0.0121 -0.0334 0.302 + 28 16.9098 1.1466 0.2292 0.2592 0.0379 0.7614 0.2264 -0.0072 0.0000 -0.0027 -0.0282 0.262 + 29 17.0696 0.9138 0.1104 0.1611 0.0446 0.5945 0.1768 -0.0102 0.0000 0.0075 -0.0175 0.207 + 30 17.1499 0.7967 0.0322 0.0548 0.0487 0.2322 0.0691 -0.0071 0.0000 0.0064 -0.0052 0.158 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.17498 Clsurf = 0.03188 - CYsurf = 0.01167 Cmsurf = -0.15087 - CDsurf = 0.00322 Cnsurf = -0.00019 - CDisurf = 0.00322 CDvsurf = 0.00000 + CLsurf = 0.17562 Clsurf = 0.03194 + CYsurf = 0.01162 Cmsurf = -0.15120 + CDsurf = 0.00313 Cnsurf = -0.00019 + CDisurf = 0.00313 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.34231 CDsurf = 0.00629 + CLsurf = 0.34354 CDsurf = 0.00610 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 2.5218 0.0846 0.4123 0.3194 0.1754 0.0000 -0.0169 0.0802 0.303 - 32 -0.1025 7.6885 1.0492 2.4045 0.0839 0.4023 0.3116 0.0369 0.0000 -0.0170 0.0777 0.304 - 33 -0.2837 7.5620 1.7073 2.3915 0.0824 0.4072 0.3155 0.0280 0.0000 -0.0158 0.0775 0.300 - 34 -0.5530 7.3741 2.3052 2.3772 0.0797 0.4153 0.3217 0.0248 0.0000 -0.0140 0.0773 0.293 - 35 -0.9075 7.1267 2.8223 2.3503 0.0757 0.4250 0.3292 0.0216 0.0000 -0.0121 0.0772 0.287 - 36 -1.3432 6.8226 3.2414 2.3053 0.0705 0.4356 0.3374 0.0190 0.0000 -0.0105 0.0776 0.281 - 37 -1.8554 6.4651 3.5491 2.2379 0.0646 0.4464 0.3458 0.0165 0.0000 -0.0095 0.0785 0.277 - 38 -2.4386 6.0582 3.7368 2.1408 0.0574 0.4559 0.3532 0.0118 0.0000 -0.0093 0.0798 0.276 - 39 -3.0862 5.6062 3.8005 2.0184 0.0472 0.4647 0.3600 0.0088 0.0000 -0.0099 0.0816 0.277 - 40 -3.7613 5.1351 3.4440 1.8771 0.0365 0.4720 0.3656 0.0045 0.0000 -0.0116 0.0842 0.282 - 41 -4.4532 4.6522 3.3149 1.7265 0.0255 0.4794 0.3713 0.0013 0.0000 -0.0145 0.0876 0.289 - 42 -5.1831 4.1429 3.0930 1.5630 0.0102 0.4875 0.3776 -0.0029 0.0000 -0.0182 0.0919 0.298 - 43 -6.0123 3.7903 3.4706 1.4116 0.0010 0.4553 0.3728 -0.0045 0.0000 -0.0201 0.1010 0.304 - 44 -6.9353 3.6075 3.3775 1.2980 0.0025 0.4399 0.3601 -0.0031 0.0000 -0.0206 0.0986 0.307 - 45 -7.8737 3.4215 3.2389 1.2018 0.0029 0.4294 0.3515 -0.0025 0.0000 -0.0206 0.0968 0.309 - 46 -8.8172 3.2345 3.0619 1.1166 0.0033 0.4220 0.3455 -0.0022 0.0000 -0.0206 0.0954 0.310 - 47 -9.7556 3.0486 2.8543 1.0388 0.0037 0.4165 0.3410 -0.0020 0.0000 -0.0205 0.0943 0.310 - 48 -10.6786 2.8657 2.6240 0.9666 0.0044 0.4123 0.3376 -0.0018 0.0000 -0.0203 0.0934 0.310 - 49 -11.5760 2.6879 2.3787 0.8988 0.0053 0.4087 0.3346 -0.0017 0.0000 -0.0202 0.0926 0.310 - 50 -12.4328 2.5181 2.1010 0.8345 0.0064 0.4051 0.3317 -0.0017 0.0000 -0.0199 0.0917 0.310 - 51 -13.2400 2.3582 1.8520 0.7728 0.0079 0.4006 0.3279 -0.0016 0.0000 -0.0196 0.0905 0.310 - 52 -13.9941 2.2087 1.6074 0.7121 0.0099 0.3941 0.3227 -0.0015 0.0000 -0.0190 0.0888 0.309 - 53 -14.6868 2.0715 1.3716 0.6509 0.0128 0.3841 0.3144 -0.0014 0.0000 -0.0181 0.0862 0.307 - 54 -15.3105 1.9479 1.1479 0.5865 0.0165 0.3680 0.3013 -0.0012 0.0000 -0.0167 0.0820 0.305 - 55 -15.8583 1.8393 0.9381 0.5156 0.0208 0.3426 0.2805 -0.0008 0.0000 -0.0150 0.0759 0.304 - 56 -16.3244 1.7470 0.7427 0.4351 0.0254 0.3044 0.2492 0.0001 0.0000 -0.0147 0.0686 0.309 - 57 -16.6722 1.4928 0.4131 0.3482 0.0304 0.7852 0.2335 -0.0031 0.0000 -0.0134 0.0340 0.307 - 58 -16.9098 1.1466 0.2292 0.2593 0.0379 0.7618 0.2266 -0.0071 0.0000 -0.0037 0.0287 0.266 - 59 -17.0696 0.9138 0.1104 0.1611 0.0445 0.5944 0.1768 -0.0101 0.0000 0.0069 0.0178 0.211 - 60 -17.1499 0.7967 0.0322 0.0547 0.0479 0.2320 0.0690 -0.0070 0.0000 0.0062 0.0053 0.160 + 31 -0.0114 7.7520 0.3539 2.5385 0.0845 0.4151 0.3215 0.1755 0.0000 -0.0183 0.0818 0.307 + 32 -0.1025 7.6885 1.0491 2.4201 0.0840 0.4049 0.3137 0.0368 0.0000 -0.0183 0.0792 0.308 + 33 -0.2837 7.5620 1.7073 2.4071 0.0827 0.4099 0.3175 0.0279 0.0000 -0.0171 0.0790 0.304 + 34 -0.5530 7.3741 2.3052 2.3925 0.0802 0.4180 0.3238 0.0241 0.0000 -0.0153 0.0788 0.297 + 35 -0.9075 7.1267 2.8223 2.3660 0.0763 0.4279 0.3314 0.0217 0.0000 -0.0134 0.0788 0.290 + 36 -1.3432 6.8226 3.2414 2.3202 0.0711 0.4385 0.3396 0.0183 0.0000 -0.0118 0.0791 0.285 + 37 -1.8554 6.4651 3.5491 2.2508 0.0652 0.4491 0.3479 0.0139 0.0000 -0.0107 0.0799 0.281 + 38 -2.4386 6.0582 3.7368 2.1552 0.0581 0.4590 0.3555 0.0121 0.0000 -0.0103 0.0811 0.279 + 39 -3.0862 5.6062 3.8005 2.0316 0.0481 0.4677 0.3623 0.0087 0.0000 -0.0108 0.0828 0.280 + 40 -3.7613 5.1351 3.4440 1.8867 0.0371 0.4744 0.3675 0.0055 0.0000 -0.0122 0.0850 0.283 + 41 -4.4532 4.6522 3.3149 1.7374 0.0254 0.4824 0.3737 0.0010 0.0000 -0.0141 0.0878 0.288 + 42 -5.1831 4.1429 3.0930 1.5668 0.0096 0.4887 0.3785 -0.0033 0.0000 -0.0172 0.0913 0.296 + 43 -6.0123 3.7903 3.4706 1.4142 0.0005 0.4562 0.3735 -0.0045 0.0000 -0.0187 0.0999 0.300 + 44 -6.9353 3.6075 3.3775 1.3001 0.0023 0.4406 0.3607 -0.0031 0.0000 -0.0190 0.0974 0.303 + 45 -7.8737 3.4215 3.2389 1.2035 0.0028 0.4300 0.3521 -0.0025 0.0000 -0.0191 0.0955 0.304 + 46 -8.8172 3.2345 3.0619 1.1181 0.0031 0.4226 0.3460 -0.0022 0.0000 -0.0190 0.0940 0.305 + 47 -9.7556 3.0486 2.8543 1.0401 0.0037 0.4170 0.3414 -0.0020 0.0000 -0.0188 0.0929 0.305 + 48 -10.6786 2.8657 2.6239 0.9677 0.0044 0.4128 0.3380 -0.0019 0.0000 -0.0187 0.0920 0.305 + 49 -11.5760 2.6879 2.3787 0.8997 0.0052 0.4092 0.3350 -0.0018 0.0000 -0.0185 0.0912 0.305 + 50 -12.4328 2.5181 2.1010 0.8353 0.0063 0.4055 0.3320 -0.0017 0.0000 -0.0183 0.0903 0.305 + 51 -13.2400 2.3582 1.8520 0.7734 0.0078 0.4009 0.3282 -0.0016 0.0000 -0.0179 0.0891 0.305 + 52 -13.9941 2.2087 1.6074 0.7126 0.0099 0.3944 0.3229 -0.0015 0.0000 -0.0173 0.0874 0.304 + 53 -14.6868 2.0715 1.3716 0.6512 0.0128 0.3843 0.3146 -0.0014 0.0000 -0.0164 0.0848 0.302 + 54 -15.3105 1.9479 1.1479 0.5867 0.0164 0.3681 0.3014 -0.0012 0.0000 -0.0150 0.0806 0.300 + 55 -15.8583 1.8393 0.9381 0.5155 0.0207 0.3426 0.2805 -0.0008 0.0000 -0.0134 0.0745 0.298 + 56 -16.3244 1.7470 0.7427 0.4347 0.0251 0.3041 0.2490 0.0001 0.0000 -0.0130 0.0671 0.302 + 57 -16.6722 1.4928 0.4131 0.3477 0.0301 0.7842 0.2332 -0.0032 0.0000 -0.0121 0.0334 0.302 + 58 -16.9098 1.1466 0.2292 0.2592 0.0379 0.7614 0.2264 -0.0072 0.0000 -0.0027 0.0282 0.262 + 59 -17.0696 0.9138 0.1104 0.1611 0.0446 0.5945 0.1768 -0.0102 0.0000 0.0075 0.0175 0.207 + 60 -17.1499 0.7967 0.0322 0.0548 0.0487 0.2322 0.0691 -0.0071 0.0000 0.0064 0.0052 0.158 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00292 Clsurf = -0.00045 - CYsurf = -0.00046 Cmsurf = -0.01488 - CDsurf = 0.00008 Cnsurf = 0.00028 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00279 Clsurf = -0.00043 + CYsurf = -0.00044 Cmsurf = -0.01423 + CDsurf = 0.00008 Cnsurf = 0.00027 CDisurf = 0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01781 CDsurf = 0.00048 + CLsurf = 0.01698 CDsurf = 0.00046 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.0029 0.0428 0.0009 0.0007 0.0000 0.0000 -0.0011 -0.0011 1.915 - 62 0.0418 4.2566 0.2392 0.0028 0.0427 0.0009 0.0007 0.0000 0.0000 -0.0011 -0.0011 1.927 - 63 0.1156 4.2274 0.3930 0.0029 0.0425 0.0009 0.0007 0.0000 0.0000 -0.0011 -0.0011 1.893 - 64 0.2254 4.1839 0.5386 0.0031 0.0422 0.0010 0.0007 0.0000 0.0000 -0.0011 -0.0011 1.796 - 65 0.3698 4.1268 0.6730 0.0034 0.0416 0.0011 0.0008 0.0000 0.0000 -0.0011 -0.0011 1.626 - 66 0.5474 4.0565 0.7936 0.0041 0.0409 0.0013 0.0010 0.0000 0.0000 -0.0012 -0.0012 1.399 - 67 0.7617 3.9717 0.9441 0.0052 0.0399 0.0017 0.0013 0.0000 0.0000 -0.0012 -0.0013 1.150 - 68 1.0116 3.8728 1.0344 0.0069 0.0386 0.0023 0.0018 0.0001 0.0000 -0.0012 -0.0014 0.916 - 69 1.2891 3.7630 1.1046 0.0096 0.0372 0.0033 0.0025 0.0001 0.0000 -0.0012 -0.0016 0.727 - 70 1.5912 3.6435 1.1542 0.0132 0.0358 0.0047 0.0036 0.0001 0.0000 -0.0012 -0.0018 0.586 - 71 1.9146 3.5155 1.1831 0.0182 0.0343 0.0067 0.0052 0.0002 0.0000 -0.0012 -0.0021 0.485 - 72 2.2558 3.3805 1.1921 0.0246 0.0328 0.0094 0.0073 0.0002 0.0000 -0.0012 -0.0025 0.414 - 73 2.6109 3.2400 1.1821 0.0322 0.0314 0.0129 0.0099 0.0003 0.0000 -0.0011 -0.0031 0.365 - 74 2.9762 3.0955 1.1548 0.0410 0.0301 0.0172 0.0132 0.0004 0.0000 -0.0011 -0.0037 0.330 - 75 3.3476 2.9485 1.1122 0.0506 0.0290 0.0222 0.0172 0.0006 0.0000 -0.0009 -0.0044 0.305 - 76 3.7210 2.8008 1.0564 0.0605 0.0280 0.0280 0.0216 0.0007 0.0000 -0.0008 -0.0053 0.286 - 77 4.0924 2.6538 0.9900 0.0701 0.0271 0.0343 0.0264 0.0008 0.0000 -0.0006 -0.0061 0.273 - 78 4.4577 2.5093 0.9155 0.0790 0.0265 0.0408 0.0315 0.0009 0.0000 -0.0004 -0.0070 0.262 - 79 4.8128 2.3687 0.8353 0.0864 0.0261 0.0473 0.0365 0.0010 0.0000 -0.0001 -0.0079 0.253 - 80 5.1540 2.2338 0.7518 0.0921 0.0258 0.0535 0.0412 0.0011 0.0000 0.0002 -0.0086 0.246 - 81 5.4774 2.1058 0.6671 0.0957 0.0258 0.0589 0.0454 0.0012 0.0000 0.0005 -0.0092 0.238 - 82 5.7795 1.9862 0.5830 0.0969 0.0260 0.0632 0.0488 0.0012 0.0000 0.0010 -0.0096 0.230 - 83 6.0570 1.8764 0.5012 0.0955 0.0263 0.0660 0.0509 0.0012 0.0000 0.0015 -0.0096 0.221 - 84 6.3069 1.7776 0.4225 0.0915 0.0268 0.0668 0.0515 0.0011 0.0000 0.0021 -0.0092 0.210 - 85 6.5264 1.6907 0.3478 0.0850 0.0273 0.0652 0.0503 0.0011 0.0000 0.0027 -0.0084 0.196 - 86 6.7314 1.6096 0.3326 0.0755 0.0278 0.0609 0.0469 0.0009 0.0000 0.0033 -0.0072 0.180 - 87 6.9144 1.5372 0.2507 0.0624 0.0283 0.0526 0.0406 0.0007 0.0000 0.0037 -0.0056 0.159 - 88 7.0535 1.4822 0.1746 0.0466 0.0287 0.0407 0.0314 0.0005 0.0000 0.0035 -0.0037 0.138 - 89 7.1471 1.4451 0.1029 0.0288 0.0290 0.0258 0.0199 0.0003 0.0000 0.0026 -0.0021 0.120 - 90 7.1941 1.4265 0.0340 0.0097 0.0292 0.0088 0.0068 0.0000 0.0000 0.0010 -0.0006 0.109 + 61 0.0047 4.2713 0.0803 -0.0012 0.0429 -0.0004 -0.0003 0.0000 0.0000 -0.0011 -0.0008 + 62 0.0418 4.2566 0.2392 -0.0012 0.0428 -0.0004 -0.0003 -0.0000 0.0000 -0.0011 -0.0009 + 63 0.1156 4.2274 0.3930 -0.0011 0.0426 -0.0004 -0.0003 -0.0000 0.0000 -0.0011 -0.0009 + 64 0.2254 4.1839 0.5386 -0.0010 0.0423 -0.0003 -0.0002 -0.0000 0.0000 -0.0011 -0.0009 + 65 0.3698 4.1268 0.6730 -0.0006 0.0417 -0.0002 -0.0001 -0.0000 0.0000 -0.0011 -0.0009 + 66 0.5474 4.0565 0.7936 0.0001 0.0410 0.0000 0.0000 -0.0000 0.0000 -0.0011 -0.0010 + 67 0.7617 3.9717 0.9441 0.0012 0.0400 0.0004 0.0003 0.0000 0.0000 -0.0012 -0.0010 + 68 1.0116 3.8728 1.0344 0.0030 0.0387 0.0010 0.0008 0.0000 0.0000 -0.0012 -0.0012 1.788 + 69 1.2891 3.7630 1.1046 0.0057 0.0373 0.0020 0.0015 0.0000 0.0000 -0.0012 -0.0013 1.054 + 70 1.5912 3.6435 1.1542 0.0095 0.0359 0.0034 0.0026 0.0001 0.0000 -0.0012 -0.0016 0.723 + 71 1.9146 3.5155 1.1831 0.0146 0.0344 0.0054 0.0042 0.0001 0.0000 -0.0012 -0.0019 0.546 + 72 2.2558 3.3805 1.1921 0.0211 0.0330 0.0081 0.0062 0.0002 0.0000 -0.0012 -0.0023 0.443 + 73 2.6109 3.2400 1.1821 0.0290 0.0316 0.0116 0.0089 0.0003 0.0000 -0.0012 -0.0029 0.379 + 74 2.9762 3.0955 1.1548 0.0381 0.0303 0.0159 0.0123 0.0004 0.0000 -0.0011 -0.0035 0.337 + 75 3.3476 2.9485 1.1122 0.0479 0.0291 0.0211 0.0162 0.0005 0.0000 -0.0010 -0.0043 0.309 + 76 3.7210 2.8008 1.0564 0.0581 0.0280 0.0269 0.0207 0.0007 0.0000 -0.0008 -0.0051 0.288 + 77 4.0924 2.6538 0.9900 0.0680 0.0272 0.0332 0.0256 0.0008 0.0000 -0.0006 -0.0060 0.274 + 78 4.4577 2.5093 0.9155 0.0772 0.0266 0.0399 0.0307 0.0009 0.0000 -0.0004 -0.0069 0.263 + 79 4.8128 2.3687 0.8353 0.0849 0.0261 0.0465 0.0358 0.0010 0.0000 -0.0001 -0.0077 0.254 + 80 5.1540 2.2338 0.7518 0.0909 0.0259 0.0527 0.0407 0.0011 0.0000 0.0002 -0.0085 0.246 + 81 5.4774 2.1058 0.6671 0.0946 0.0259 0.0583 0.0449 0.0012 0.0000 0.0005 -0.0091 0.238 + 82 5.7795 1.9862 0.5830 0.0960 0.0260 0.0627 0.0483 0.0012 0.0000 0.0010 -0.0095 0.230 + 83 6.0570 1.8764 0.5012 0.0948 0.0264 0.0655 0.0505 0.0012 0.0000 0.0015 -0.0095 0.221 + 84 6.3069 1.7776 0.4225 0.0910 0.0268 0.0663 0.0512 0.0011 0.0000 0.0021 -0.0092 0.209 + 85 6.5264 1.6907 0.3478 0.0845 0.0273 0.0648 0.0500 0.0011 0.0000 0.0027 -0.0084 0.196 + 86 6.7314 1.6096 0.3326 0.0752 0.0278 0.0606 0.0467 0.0009 0.0000 0.0033 -0.0072 0.180 + 87 6.9144 1.5372 0.2507 0.0621 0.0283 0.0524 0.0404 0.0007 0.0000 0.0037 -0.0055 0.159 + 88 7.0535 1.4822 0.1746 0.0464 0.0287 0.0406 0.0313 0.0005 0.0000 0.0035 -0.0037 0.138 + 89 7.1471 1.4451 0.1029 0.0287 0.0290 0.0257 0.0198 0.0003 0.0000 0.0026 -0.0020 0.119 + 90 7.1941 1.4265 0.0340 0.0097 0.0292 0.0088 0.0068 0.0000 0.0000 0.0010 -0.0006 0.108 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00292 Clsurf = 0.00045 - CYsurf = 0.00046 Cmsurf = -0.01488 - CDsurf = 0.00008 Cnsurf = -0.00028 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00279 Clsurf = 0.00043 + CYsurf = 0.00044 Cmsurf = -0.01423 + CDsurf = 0.00008 Cnsurf = -0.00027 CDisurf = 0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01781 CDsurf = 0.00048 + CLsurf = 0.01698 CDsurf = 0.00046 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.0029 0.0428 0.0009 0.0007 0.0000 0.0000 -0.0011 0.0011 1.915 - 92 -0.0418 4.2566 0.2392 0.0028 0.0427 0.0009 0.0007 0.0000 0.0000 -0.0011 0.0011 1.927 - 93 -0.1156 4.2274 0.3930 0.0029 0.0425 0.0009 0.0007 0.0000 0.0000 -0.0011 0.0011 1.892 - 94 -0.2254 4.1839 0.5386 0.0031 0.0422 0.0010 0.0007 0.0000 0.0000 -0.0011 0.0011 1.796 - 95 -0.3698 4.1268 0.6730 0.0034 0.0416 0.0011 0.0008 0.0000 0.0000 -0.0011 0.0011 1.626 - 96 -0.5474 4.0565 0.7936 0.0041 0.0409 0.0013 0.0010 0.0000 0.0000 -0.0012 0.0012 1.399 - 97 -0.7617 3.9717 0.9441 0.0052 0.0399 0.0017 0.0013 0.0000 0.0000 -0.0012 0.0013 1.150 - 98 -1.0116 3.8728 1.0344 0.0069 0.0386 0.0023 0.0018 0.0001 0.0000 -0.0012 0.0014 0.916 - 99 -1.2891 3.7630 1.1046 0.0096 0.0372 0.0033 0.0025 0.0001 0.0000 -0.0012 0.0016 0.727 - 100 -1.5912 3.6435 1.1542 0.0133 0.0358 0.0047 0.0036 0.0001 0.0000 -0.0012 0.0018 0.586 - 101 -1.9146 3.5155 1.1831 0.0182 0.0343 0.0067 0.0052 0.0002 0.0000 -0.0012 0.0021 0.485 - 102 -2.2558 3.3805 1.1921 0.0246 0.0328 0.0094 0.0073 0.0002 0.0000 -0.0012 0.0025 0.414 - 103 -2.6109 3.2400 1.1821 0.0322 0.0314 0.0129 0.0099 0.0003 0.0000 -0.0011 0.0031 0.365 - 104 -2.9762 3.0955 1.1548 0.0410 0.0301 0.0172 0.0132 0.0004 0.0000 -0.0011 0.0037 0.330 - 105 -3.3476 2.9485 1.1122 0.0506 0.0290 0.0222 0.0172 0.0006 0.0000 -0.0009 0.0044 0.305 - 106 -3.7210 2.8008 1.0564 0.0605 0.0280 0.0280 0.0216 0.0007 0.0000 -0.0008 0.0053 0.286 - 107 -4.0924 2.6538 0.9900 0.0701 0.0271 0.0343 0.0264 0.0008 0.0000 -0.0006 0.0061 0.273 - 108 -4.4577 2.5093 0.9155 0.0790 0.0265 0.0408 0.0315 0.0009 0.0000 -0.0004 0.0070 0.262 - 109 -4.8128 2.3687 0.8353 0.0864 0.0261 0.0473 0.0365 0.0010 0.0000 -0.0001 0.0079 0.253 - 110 -5.1540 2.2338 0.7518 0.0921 0.0258 0.0535 0.0412 0.0011 0.0000 0.0002 0.0086 0.246 - 111 -5.4774 2.1058 0.6671 0.0957 0.0258 0.0589 0.0454 0.0012 0.0000 0.0005 0.0092 0.238 - 112 -5.7795 1.9862 0.5830 0.0969 0.0260 0.0632 0.0488 0.0012 0.0000 0.0010 0.0096 0.230 - 113 -6.0570 1.8764 0.5012 0.0955 0.0263 0.0660 0.0509 0.0012 0.0000 0.0015 0.0096 0.221 - 114 -6.3069 1.7776 0.4225 0.0915 0.0268 0.0668 0.0515 0.0011 0.0000 0.0021 0.0092 0.210 - 115 -6.5264 1.6907 0.3478 0.0850 0.0273 0.0652 0.0503 0.0011 0.0000 0.0027 0.0084 0.196 - 116 -6.7314 1.6096 0.3326 0.0755 0.0278 0.0609 0.0469 0.0009 0.0000 0.0033 0.0072 0.180 - 117 -6.9144 1.5372 0.2507 0.0624 0.0283 0.0526 0.0406 0.0007 0.0000 0.0037 0.0056 0.159 - 118 -7.0535 1.4822 0.1746 0.0466 0.0287 0.0407 0.0314 0.0005 0.0000 0.0035 0.0037 0.138 - 119 -7.1471 1.4451 0.1029 0.0288 0.0290 0.0258 0.0199 0.0003 0.0000 0.0026 0.0021 0.120 - 120 -7.1941 1.4265 0.0340 0.0097 0.0292 0.0088 0.0068 0.0000 0.0000 0.0010 0.0006 0.109 + 91 -0.0047 4.2713 0.0803 -0.0012 0.0429 -0.0004 -0.0003 0.0000 0.0000 -0.0011 0.0008 + 92 -0.0418 4.2566 0.2392 -0.0012 0.0428 -0.0004 -0.0003 -0.0000 0.0000 -0.0011 0.0009 + 93 -0.1156 4.2274 0.3930 -0.0011 0.0426 -0.0004 -0.0003 -0.0000 0.0000 -0.0011 0.0009 + 94 -0.2254 4.1839 0.5386 -0.0010 0.0423 -0.0003 -0.0002 -0.0000 0.0000 -0.0011 0.0009 + 95 -0.3698 4.1268 0.6730 -0.0006 0.0417 -0.0002 -0.0001 -0.0000 0.0000 -0.0011 0.0009 + 96 -0.5474 4.0565 0.7936 0.0001 0.0410 0.0000 0.0000 -0.0000 0.0000 -0.0011 0.0010 + 97 -0.7617 3.9717 0.9441 0.0012 0.0400 0.0004 0.0003 0.0000 0.0000 -0.0012 0.0010 + 98 -1.0116 3.8728 1.0344 0.0030 0.0387 0.0010 0.0008 0.0000 0.0000 -0.0012 0.0012 1.788 + 99 -1.2891 3.7630 1.1046 0.0057 0.0373 0.0020 0.0015 0.0000 0.0000 -0.0012 0.0013 1.054 + 100 -1.5912 3.6435 1.1542 0.0095 0.0359 0.0034 0.0026 0.0001 0.0000 -0.0012 0.0016 0.723 + 101 -1.9146 3.5155 1.1831 0.0146 0.0344 0.0054 0.0042 0.0001 0.0000 -0.0012 0.0019 0.546 + 102 -2.2558 3.3805 1.1921 0.0211 0.0330 0.0081 0.0062 0.0002 0.0000 -0.0012 0.0023 0.443 + 103 -2.6109 3.2400 1.1821 0.0290 0.0316 0.0116 0.0089 0.0003 0.0000 -0.0012 0.0029 0.379 + 104 -2.9762 3.0955 1.1548 0.0381 0.0303 0.0159 0.0123 0.0004 0.0000 -0.0011 0.0035 0.337 + 105 -3.3476 2.9485 1.1122 0.0479 0.0291 0.0211 0.0162 0.0005 0.0000 -0.0010 0.0043 0.309 + 106 -3.7210 2.8008 1.0564 0.0581 0.0280 0.0269 0.0207 0.0007 0.0000 -0.0008 0.0051 0.288 + 107 -4.0924 2.6538 0.9900 0.0680 0.0272 0.0332 0.0256 0.0008 0.0000 -0.0006 0.0060 0.274 + 108 -4.4577 2.5093 0.9155 0.0772 0.0266 0.0399 0.0307 0.0009 0.0000 -0.0004 0.0069 0.263 + 109 -4.8128 2.3687 0.8353 0.0849 0.0261 0.0465 0.0358 0.0010 0.0000 -0.0001 0.0077 0.254 + 110 -5.1540 2.2338 0.7518 0.0909 0.0259 0.0527 0.0407 0.0011 0.0000 0.0002 0.0085 0.246 + 111 -5.4774 2.1058 0.6671 0.0946 0.0259 0.0583 0.0449 0.0012 0.0000 0.0005 0.0091 0.238 + 112 -5.7795 1.9862 0.5830 0.0960 0.0260 0.0627 0.0483 0.0012 0.0000 0.0010 0.0095 0.230 + 113 -6.0570 1.8764 0.5012 0.0948 0.0264 0.0655 0.0505 0.0012 0.0000 0.0015 0.0095 0.221 + 114 -6.3069 1.7776 0.4225 0.0910 0.0268 0.0663 0.0512 0.0011 0.0000 0.0021 0.0092 0.209 + 115 -6.5264 1.6907 0.3478 0.0845 0.0273 0.0648 0.0500 0.0011 0.0000 0.0027 0.0084 0.196 + 116 -6.7314 1.6096 0.3326 0.0752 0.0278 0.0606 0.0467 0.0009 0.0000 0.0033 0.0072 0.180 + 117 -6.9144 1.5372 0.2507 0.0621 0.0283 0.0524 0.0404 0.0007 0.0000 0.0037 0.0055 0.159 + 118 -7.0535 1.4822 0.1746 0.0464 0.0287 0.0406 0.0313 0.0005 0.0000 0.0035 0.0037 0.138 + 119 -7.1471 1.4451 0.1029 0.0287 0.0290 0.0257 0.0198 0.0003 0.0000 0.0026 0.0020 0.119 + 120 -7.1941 1.4265 0.0340 0.0097 0.0292 0.0088 0.0068 0.0000 0.0000 0.0010 0.0006 0.108 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,66 +198,66 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.221 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.206 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.215 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.219 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.212 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.214 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.224 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.222 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.209 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.229 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.233 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.245 + 128 0.0000 6.6646 2.2808 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.242 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.253 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.209 + 133 0.0000 3.9932 1.6033 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 + 134 0.0000 3.7615 1.5362 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.188 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.185 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.169 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.149 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.130 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.122 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.143 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.131 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00047 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.01657 + CLsurf = -0.00054 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.01664 CDsurf = -0.00012 Cnsurf = -0.00000 CDisurf = -0.00012 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00047 CDsurf = -0.00012 + CLsurf = -0.00054 CDsurf = -0.00012 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.0233 0.0468 -0.0107 -0.0009 -0.0006 0.0000 0.0020 0.0003 - 152 -1.3090 31.2096 11.6724 -0.0214 0.0550 -0.0026 -0.0007 -0.0002 0.0000 0.0022 0.0006 - 153 -0.9350 34.0626 12.7394 -0.0160 0.0608 -0.0011 -0.0005 -0.0001 0.0000 0.0022 0.0008 - 154 -0.5610 36.1619 13.5246 -0.0106 0.0650 -0.0005 -0.0003 0.0000 0.0000 0.0022 0.0010 - 155 -0.1870 37.5332 14.0374 -0.0072 0.0676 -0.0002 -0.0002 0.0001 0.0000 0.0022 0.0015 - 156 0.1870 37.5332 14.0374 -0.0072 0.0676 -0.0002 -0.0002 0.0001 0.0000 0.0022 0.0015 - 157 0.5610 36.1619 13.5246 -0.0106 0.0650 -0.0005 -0.0003 0.0000 0.0000 0.0022 0.0010 - 158 0.9350 34.0626 12.7394 -0.0160 0.0608 -0.0011 -0.0005 -0.0001 0.0000 0.0022 0.0008 - 159 1.3090 31.2096 11.6724 -0.0214 0.0550 -0.0026 -0.0007 -0.0002 0.0000 0.0022 0.0006 - 160 1.6830 26.5957 9.9468 -0.0233 0.0468 -0.0107 -0.0009 -0.0006 0.0000 0.0020 0.0003 + 151 -1.6830 26.5957 9.9468 -0.0251 0.0467 -0.0115 -0.0009 -0.0006 0.0000 0.0020 0.0003 + 152 -1.3090 31.2096 11.6724 -0.0238 0.0551 -0.0029 -0.0008 -0.0002 0.0000 0.0022 0.0006 + 153 -0.9350 34.0626 12.7394 -0.0185 0.0610 -0.0013 -0.0005 -0.0001 0.0000 0.0023 0.0008 + 154 -0.5610 36.1619 13.5246 -0.0131 0.0652 -0.0006 -0.0004 0.0000 0.0000 0.0022 0.0010 + 155 -0.1870 37.5332 14.0374 -0.0097 0.0678 -0.0003 -0.0003 0.0001 0.0000 0.0022 0.0016 + 156 0.1870 37.5332 14.0374 -0.0097 0.0678 -0.0003 -0.0003 0.0001 0.0000 0.0022 0.0016 + 157 0.5610 36.1619 13.5246 -0.0131 0.0652 -0.0006 -0.0004 0.0000 0.0000 0.0022 0.0010 + 158 0.9350 34.0626 12.7394 -0.0185 0.0610 -0.0013 -0.0005 -0.0001 0.0000 0.0023 0.0008 + 159 1.3090 31.2096 11.6724 -0.0238 0.0551 -0.0029 -0.0008 -0.0002 0.0000 0.0022 0.0006 + 160 1.6830 26.5957 9.9468 -0.0251 0.0467 -0.0115 -0.0009 -0.0006 0.0000 0.0020 0.0003 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = 0.00000 + CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 CDisurf = -0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.496 - 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.472 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.476 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.491 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.536 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.546 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.546 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.549 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.590 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.376 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.395 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.453 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.458 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.490 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.530 + 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.556 + 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.550 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.551 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.576 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_03_04.txt b/regression/scripts/AVL/avl_files/strip_forces_case_03_04.txt index cd0c59a99d..a4403208f7 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_03_04.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_03_04.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.29889 Clsurf = -0.05740 - CYsurf = -0.01791 Cmsurf = -0.26604 - CDsurf = 0.00823 Cnsurf = -0.00311 - CDisurf = 0.00823 CDvsurf = 0.00000 + CLsurf = 0.29955 Clsurf = -0.05746 + CYsurf = -0.01775 Cmsurf = -0.26636 + CDsurf = 0.00798 Cnsurf = -0.00313 + CDisurf = 0.00798 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.58444 CDsurf = 0.01607 + CLsurf = 0.58569 CDsurf = 0.01557 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 3.9416 0.1384 0.6139 0.4752 0.4017 0.0000 -0.0262 -0.1257 0.305 - 2 0.1025 7.6885 1.0492 3.6701 0.1380 0.6098 0.4721 0.0810 0.0000 -0.0264 -0.1195 0.306 - 3 0.2837 7.5620 1.7073 3.6451 0.1365 0.6181 0.4785 0.0609 0.0000 -0.0245 -0.1189 0.301 - 4 0.5530 7.3741 2.3052 3.6270 0.1337 0.6317 0.4890 0.0541 0.0000 -0.0216 -0.1186 0.294 - 5 0.9075 7.1267 2.8223 3.5952 0.1286 0.6487 0.5022 0.0478 0.0000 -0.0185 -0.1187 0.287 - 6 1.3432 6.8226 3.2414 3.5432 0.1188 0.6685 0.5176 0.0429 0.0000 -0.0158 -0.1195 0.281 - 7 1.8554 6.4651 3.5491 3.4660 0.1012 0.6908 0.5348 0.0383 0.0000 -0.0137 -0.1212 0.276 - 8 2.4386 6.0582 3.7368 3.3500 0.0831 0.7138 0.5526 0.0287 0.0000 -0.0127 -0.1239 0.273 - 9 3.0862 5.6062 3.8005 3.2060 0.0708 0.7389 0.5720 0.0233 0.0000 -0.0127 -0.1278 0.272 - 10 3.7613 5.1351 3.4440 3.0357 0.0594 0.7649 0.5921 0.0148 0.0000 -0.0141 -0.1329 0.274 - 11 4.4532 4.6522 3.3149 2.8529 0.0466 0.7943 0.6149 0.0082 0.0000 -0.0166 -0.1395 0.277 - 12 5.1831 4.1429 3.0930 2.6483 0.0275 0.8291 0.6418 -0.0012 0.0000 -0.0197 -0.1473 0.281 - 13 6.0123 3.7903 3.4706 2.4503 0.0151 0.7958 0.6494 -0.0052 0.0000 -0.0194 -0.1626 0.280 - 14 6.9353 3.6075 3.3775 2.2967 0.0146 0.7835 0.6394 -0.0031 0.0000 -0.0197 -0.1607 0.281 - 15 7.8737 3.4215 3.2389 2.1603 0.0127 0.7770 0.6340 -0.0026 0.0000 -0.0197 -0.1595 0.281 - 16 8.8172 3.2345 3.0619 2.0338 0.0114 0.7738 0.6314 -0.0025 0.0000 -0.0195 -0.1588 0.281 - 17 9.7556 3.0486 2.8543 1.9127 0.0114 0.7721 0.6300 -0.0026 0.0000 -0.0193 -0.1583 0.281 - 18 10.6786 2.8657 2.6240 1.7959 0.0122 0.7712 0.6293 -0.0027 0.0000 -0.0191 -0.1580 0.280 - 19 11.5760 2.6879 2.3787 1.6824 0.0136 0.7703 0.6285 -0.0029 0.0000 -0.0188 -0.1575 0.280 - 20 12.4328 2.5181 2.1010 1.5715 0.0156 0.7680 0.6267 -0.0031 0.0000 -0.0183 -0.1567 0.279 - 21 13.2400 2.3582 1.8520 1.4623 0.0184 0.7631 0.6227 -0.0032 0.0000 -0.0176 -0.1552 0.278 - 22 13.9941 2.2087 1.6074 1.3525 0.0223 0.7536 0.6150 -0.0033 0.0000 -0.0165 -0.1524 0.277 - 23 14.6868 2.0715 1.3716 1.2393 0.0276 0.7363 0.6008 -0.0031 0.0000 -0.0148 -0.1477 0.275 - 24 15.3105 1.9479 1.1479 1.1182 0.0345 0.7065 0.5765 -0.0027 0.0000 -0.0122 -0.1400 0.271 - 25 15.8583 1.8393 0.9381 0.9827 0.0423 0.6574 0.5365 -0.0016 0.0000 -0.0094 -0.1286 0.268 - 26 16.3244 1.7470 0.7427 0.8281 0.0503 0.5829 0.4756 0.0020 0.0000 -0.0101 -0.1156 0.271 - 27 16.6722 1.4928 0.4131 0.6606 0.0589 1.4978 0.4453 -0.0120 0.0000 -0.0110 -0.0593 0.275 - 28 16.9098 1.1466 0.2292 0.4899 0.0711 1.4510 0.4313 -0.0274 0.0000 0.0067 -0.0493 0.234 - 29 17.0696 0.9138 0.1104 0.3030 0.0811 1.1315 0.3364 -0.0392 0.0000 0.0241 -0.0296 0.178 - 30 17.1499 0.7967 0.0322 0.1027 0.0863 0.4438 0.1319 -0.0287 0.0000 0.0165 -0.0082 0.125 + 1 0.0114 7.7520 0.3539 3.9590 0.1384 0.6167 0.4774 0.4021 0.0000 -0.0277 -0.1273 0.308 + 2 0.1025 7.6885 1.0491 3.6856 0.1380 0.6124 0.4741 0.0809 0.0000 -0.0277 -0.1209 0.308 + 3 0.2837 7.5620 1.7073 3.6606 0.1368 0.6208 0.4806 0.0605 0.0000 -0.0258 -0.1204 0.304 + 4 0.5530 7.3741 2.3052 3.6414 0.1342 0.6344 0.4911 0.0525 0.0000 -0.0229 -0.1201 0.297 + 5 0.9075 7.1267 2.8223 3.6106 0.1292 0.6515 0.5044 0.0479 0.0000 -0.0199 -0.1202 0.289 + 6 1.3432 6.8226 3.2414 3.5569 0.1194 0.6714 0.5197 0.0411 0.0000 -0.0171 -0.1210 0.283 + 7 1.8554 6.4651 3.5491 3.4757 0.1018 0.6935 0.5369 0.0321 0.0000 -0.0150 -0.1226 0.278 + 8 2.4386 6.0582 3.7368 3.3647 0.0837 0.7169 0.5550 0.0291 0.0000 -0.0137 -0.1252 0.275 + 9 3.0862 5.6062 3.8005 3.2190 0.0717 0.7419 0.5744 0.0230 0.0000 -0.0136 -0.1290 0.274 + 10 3.7613 5.1351 3.4440 3.0430 0.0600 0.7665 0.5934 0.0167 0.0000 -0.0148 -0.1337 0.275 + 11 4.4532 4.6522 3.3149 2.8686 0.0465 0.7988 0.6183 0.0073 0.0000 -0.0159 -0.1395 0.276 + 12 5.1831 4.1429 3.0930 2.6519 0.0269 0.8303 0.6428 -0.0022 0.0000 -0.0186 -0.1466 0.279 + 13 6.0123 3.7903 3.4706 2.4530 0.0146 0.7967 0.6501 -0.0052 0.0000 -0.0179 -0.1615 0.278 + 14 6.9353 3.6075 3.3775 2.2985 0.0144 0.7841 0.6399 -0.0031 0.0000 -0.0182 -0.1595 0.278 + 15 7.8737 3.4215 3.2389 2.1619 0.0125 0.7776 0.6345 -0.0026 0.0000 -0.0181 -0.1582 0.279 + 16 8.8172 3.2345 3.0619 2.0353 0.0113 0.7743 0.6319 -0.0025 0.0000 -0.0179 -0.1575 0.278 + 17 9.7556 3.0486 2.8543 1.9140 0.0113 0.7726 0.6304 -0.0026 0.0000 -0.0177 -0.1570 0.278 + 18 10.6786 2.8657 2.6239 1.7970 0.0122 0.7717 0.6297 -0.0028 0.0000 -0.0175 -0.1566 0.278 + 19 11.5760 2.6879 2.3787 1.6833 0.0136 0.7707 0.6289 -0.0030 0.0000 -0.0172 -0.1561 0.277 + 20 12.4328 2.5181 2.1010 1.5723 0.0156 0.7684 0.6270 -0.0032 0.0000 -0.0167 -0.1553 0.277 + 21 13.2400 2.3582 1.8520 1.4629 0.0184 0.7635 0.6230 -0.0033 0.0000 -0.0160 -0.1538 0.276 + 22 13.9941 2.2087 1.6074 1.3531 0.0222 0.7539 0.6152 -0.0033 0.0000 -0.0149 -0.1511 0.274 + 23 14.6868 2.0715 1.3716 1.2397 0.0276 0.7365 0.6010 -0.0031 0.0000 -0.0131 -0.1463 0.272 + 24 15.3105 1.9479 1.1479 1.1183 0.0344 0.7066 0.5766 -0.0027 0.0000 -0.0105 -0.1385 0.268 + 25 15.8583 1.8393 0.9381 0.9827 0.0422 0.6574 0.5365 -0.0017 0.0000 -0.0078 -0.1271 0.265 + 26 16.3244 1.7470 0.7427 0.8276 0.0500 0.5826 0.4754 0.0019 0.0000 -0.0085 -0.1142 0.268 + 27 16.6722 1.4928 0.4131 0.6601 0.0586 1.4969 0.4450 -0.0122 0.0000 -0.0097 -0.0587 0.272 + 28 16.9098 1.1466 0.2292 0.4898 0.0710 1.4506 0.4312 -0.0276 0.0000 0.0077 -0.0488 0.232 + 29 17.0696 0.9138 0.1104 0.3030 0.0813 1.1316 0.3364 -0.0394 0.0000 0.0247 -0.0293 0.176 + 30 17.1499 0.7967 0.0322 0.1027 0.0870 0.4441 0.1320 -0.0290 0.0000 0.0166 -0.0082 0.124 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.29889 Clsurf = 0.05740 - CYsurf = 0.01791 Cmsurf = -0.26604 - CDsurf = 0.00823 Cnsurf = 0.00311 - CDisurf = 0.00823 CDvsurf = 0.00000 + CLsurf = 0.29955 Clsurf = 0.05746 + CYsurf = 0.01775 Cmsurf = -0.26636 + CDsurf = 0.00798 Cnsurf = 0.00313 + CDisurf = 0.00798 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.58443 CDsurf = 0.01607 + CLsurf = 0.58569 CDsurf = 0.01557 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 3.9416 0.1385 0.6139 0.4752 0.4017 0.0000 -0.0262 0.1257 0.305 - 32 -0.1025 7.6885 1.0492 3.6701 0.1380 0.6098 0.4721 0.0810 0.0000 -0.0264 0.1195 0.306 - 33 -0.2837 7.5620 1.7073 3.6451 0.1365 0.6181 0.4785 0.0609 0.0000 -0.0245 0.1189 0.301 - 34 -0.5530 7.3741 2.3052 3.6270 0.1337 0.6317 0.4890 0.0541 0.0000 -0.0216 0.1186 0.294 - 35 -0.9075 7.1267 2.8223 3.5951 0.1286 0.6487 0.5022 0.0478 0.0000 -0.0185 0.1187 0.287 - 36 -1.3432 6.8226 3.2414 3.5432 0.1188 0.6685 0.5176 0.0429 0.0000 -0.0158 0.1195 0.281 - 37 -1.8554 6.4651 3.5491 3.4660 0.1012 0.6908 0.5348 0.0383 0.0000 -0.0137 0.1212 0.276 - 38 -2.4386 6.0582 3.7368 3.3500 0.0831 0.7138 0.5526 0.0287 0.0000 -0.0127 0.1239 0.273 - 39 -3.0862 5.6062 3.8005 3.2060 0.0708 0.7389 0.5720 0.0233 0.0000 -0.0127 0.1278 0.272 - 40 -3.7613 5.1351 3.4440 3.0356 0.0594 0.7649 0.5921 0.0147 0.0000 -0.0141 0.1328 0.274 - 41 -4.4532 4.6522 3.3149 2.8529 0.0466 0.7943 0.6149 0.0082 0.0000 -0.0166 0.1395 0.277 - 42 -5.1831 4.1429 3.0930 2.6482 0.0275 0.8291 0.6418 -0.0012 0.0000 -0.0197 0.1473 0.281 - 43 -6.0123 3.7903 3.4706 2.4502 0.0151 0.7958 0.6494 -0.0052 0.0000 -0.0194 0.1626 0.280 - 44 -6.9353 3.6075 3.3775 2.2967 0.0146 0.7835 0.6394 -0.0031 0.0000 -0.0197 0.1607 0.281 - 45 -7.8737 3.4215 3.2389 2.1603 0.0127 0.7770 0.6340 -0.0026 0.0000 -0.0197 0.1595 0.281 - 46 -8.8172 3.2345 3.0619 2.0338 0.0114 0.7738 0.6314 -0.0025 0.0000 -0.0195 0.1588 0.281 - 47 -9.7556 3.0486 2.8543 1.9126 0.0114 0.7721 0.6300 -0.0026 0.0000 -0.0193 0.1583 0.281 - 48 -10.6786 2.8657 2.6240 1.7959 0.0122 0.7712 0.6293 -0.0027 0.0000 -0.0191 0.1580 0.280 - 49 -11.5760 2.6879 2.3787 1.6824 0.0136 0.7703 0.6285 -0.0029 0.0000 -0.0188 0.1575 0.280 - 50 -12.4328 2.5181 2.1010 1.5715 0.0156 0.7680 0.6267 -0.0031 0.0000 -0.0183 0.1567 0.279 - 51 -13.2400 2.3582 1.8520 1.4623 0.0184 0.7631 0.6227 -0.0032 0.0000 -0.0176 0.1552 0.278 - 52 -13.9941 2.2087 1.6074 1.3525 0.0223 0.7536 0.6150 -0.0033 0.0000 -0.0165 0.1524 0.277 - 53 -14.6868 2.0715 1.3716 1.2393 0.0276 0.7363 0.6008 -0.0031 0.0000 -0.0148 0.1477 0.275 - 54 -15.3105 1.9479 1.1479 1.1182 0.0345 0.7065 0.5765 -0.0027 0.0000 -0.0122 0.1400 0.271 - 55 -15.8583 1.8393 0.9381 0.9827 0.0423 0.6574 0.5365 -0.0016 0.0000 -0.0094 0.1286 0.268 - 56 -16.3244 1.7470 0.7427 0.8281 0.0503 0.5829 0.4756 0.0020 0.0000 -0.0101 0.1156 0.271 - 57 -16.6722 1.4928 0.4131 0.6606 0.0589 1.4978 0.4453 -0.0120 0.0000 -0.0110 0.0593 0.275 - 58 -16.9098 1.1466 0.2292 0.4899 0.0711 1.4510 0.4313 -0.0274 0.0000 0.0067 0.0493 0.234 - 59 -17.0696 0.9138 0.1104 0.3030 0.0811 1.1315 0.3364 -0.0392 0.0000 0.0241 0.0296 0.178 - 60 -17.1499 0.7967 0.0322 0.1027 0.0863 0.4437 0.1319 -0.0287 0.0000 0.0165 0.0082 0.125 + 31 -0.0114 7.7520 0.3539 3.9590 0.1384 0.6167 0.4774 0.4021 0.0000 -0.0277 0.1273 0.308 + 32 -0.1025 7.6885 1.0491 3.6856 0.1380 0.6124 0.4741 0.0809 0.0000 -0.0277 0.1209 0.308 + 33 -0.2837 7.5620 1.7073 3.6606 0.1368 0.6208 0.4806 0.0605 0.0000 -0.0258 0.1204 0.304 + 34 -0.5530 7.3741 2.3052 3.6414 0.1342 0.6344 0.4911 0.0525 0.0000 -0.0229 0.1201 0.297 + 35 -0.9075 7.1267 2.8223 3.6106 0.1292 0.6515 0.5044 0.0479 0.0000 -0.0199 0.1202 0.289 + 36 -1.3432 6.8226 3.2414 3.5569 0.1194 0.6714 0.5197 0.0411 0.0000 -0.0171 0.1210 0.283 + 37 -1.8554 6.4651 3.5491 3.4757 0.1018 0.6935 0.5369 0.0321 0.0000 -0.0150 0.1226 0.278 + 38 -2.4386 6.0582 3.7368 3.3647 0.0837 0.7169 0.5550 0.0291 0.0000 -0.0137 0.1252 0.275 + 39 -3.0862 5.6062 3.8005 3.2190 0.0717 0.7419 0.5744 0.0230 0.0000 -0.0136 0.1290 0.274 + 40 -3.7613 5.1351 3.4440 3.0430 0.0600 0.7665 0.5934 0.0167 0.0000 -0.0148 0.1337 0.275 + 41 -4.4532 4.6522 3.3149 2.8686 0.0465 0.7988 0.6183 0.0073 0.0000 -0.0159 0.1395 0.276 + 42 -5.1831 4.1429 3.0930 2.6519 0.0269 0.8303 0.6428 -0.0022 0.0000 -0.0186 0.1466 0.279 + 43 -6.0123 3.7903 3.4706 2.4530 0.0146 0.7967 0.6501 -0.0052 0.0000 -0.0179 0.1615 0.278 + 44 -6.9353 3.6075 3.3775 2.2985 0.0144 0.7841 0.6399 -0.0031 0.0000 -0.0182 0.1595 0.278 + 45 -7.8737 3.4215 3.2389 2.1619 0.0125 0.7776 0.6345 -0.0026 0.0000 -0.0181 0.1582 0.279 + 46 -8.8172 3.2345 3.0619 2.0353 0.0113 0.7743 0.6319 -0.0025 0.0000 -0.0179 0.1575 0.278 + 47 -9.7556 3.0486 2.8543 1.9140 0.0113 0.7726 0.6304 -0.0026 0.0000 -0.0177 0.1570 0.278 + 48 -10.6786 2.8657 2.6239 1.7970 0.0122 0.7717 0.6297 -0.0028 0.0000 -0.0175 0.1566 0.278 + 49 -11.5760 2.6879 2.3787 1.6833 0.0136 0.7707 0.6289 -0.0030 0.0000 -0.0172 0.1561 0.277 + 50 -12.4328 2.5181 2.1010 1.5723 0.0156 0.7684 0.6270 -0.0032 0.0000 -0.0167 0.1553 0.277 + 51 -13.2400 2.3582 1.8520 1.4629 0.0184 0.7635 0.6230 -0.0033 0.0000 -0.0160 0.1538 0.276 + 52 -13.9941 2.2087 1.6074 1.3531 0.0222 0.7539 0.6152 -0.0033 0.0000 -0.0149 0.1511 0.274 + 53 -14.6868 2.0715 1.3716 1.2397 0.0276 0.7365 0.6010 -0.0031 0.0000 -0.0131 0.1463 0.272 + 54 -15.3105 1.9479 1.1479 1.1183 0.0344 0.7066 0.5766 -0.0027 0.0000 -0.0105 0.1385 0.268 + 55 -15.8583 1.8393 0.9381 0.9827 0.0422 0.6574 0.5365 -0.0017 0.0000 -0.0078 0.1271 0.265 + 56 -16.3244 1.7470 0.7427 0.8276 0.0500 0.5826 0.4754 0.0019 0.0000 -0.0085 0.1142 0.268 + 57 -16.6722 1.4928 0.4131 0.6601 0.0586 1.4969 0.4450 -0.0122 0.0000 -0.0097 0.0587 0.272 + 58 -16.9098 1.1466 0.2292 0.4898 0.0710 1.4506 0.4312 -0.0276 0.0000 0.0077 0.0488 0.232 + 59 -17.0696 0.9138 0.1104 0.3030 0.0813 1.1316 0.3364 -0.0394 0.0000 0.0247 0.0293 0.176 + 60 -17.1499 0.7967 0.0322 0.1027 0.0870 0.4441 0.1320 -0.0290 0.0000 0.0166 0.0082 0.124 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02635 Clsurf = -0.00282 - CYsurf = -0.00418 Cmsurf = -0.12887 - CDsurf = 0.00152 Cnsurf = 0.00238 - CDisurf = 0.00152 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02621 Clsurf = -0.00281 + CYsurf = -0.00416 Cmsurf = -0.12823 + CDsurf = 0.00151 Cnsurf = 0.00237 + CDisurf = 0.00151 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16056 CDsurf = 0.00912 + CLsurf = 0.15974 CDsurf = 0.00909 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.5550 0.0904 0.1658 0.1270 0.0391 0.0000 -0.0075 -0.0343 0.309 - 62 0.0418 4.2566 0.2392 0.5115 0.0906 0.1562 0.1196 0.0112 0.0000 -0.0074 -0.0322 0.312 - 63 0.1156 4.2274 0.3930 0.5085 0.0906 0.1565 0.1199 0.0094 0.0000 -0.0071 -0.0319 0.309 - 64 0.2254 4.1839 0.5386 0.5077 0.0901 0.1580 0.1210 0.0090 0.0000 -0.0064 -0.0316 0.303 - 65 0.3698 4.1268 0.6730 0.5077 0.0892 0.1602 0.1227 0.0089 0.0000 -0.0057 -0.0313 0.296 - 66 0.5474 4.0565 0.7936 0.5078 0.0877 0.1630 0.1249 0.0088 0.0000 -0.0049 -0.0311 0.289 - 67 0.7617 3.9717 0.9441 0.5073 0.0854 0.1664 0.1274 0.0088 0.0000 -0.0041 -0.0310 0.282 - 68 1.0116 3.8728 1.0344 0.5070 0.0822 0.1706 0.1306 0.0088 0.0000 -0.0034 -0.0311 0.276 - 69 1.2891 3.7630 1.1046 0.5061 0.0782 0.1752 0.1342 0.0089 0.0000 -0.0028 -0.0314 0.271 - 70 1.5912 3.6435 1.1542 0.5056 0.0739 0.1808 0.1385 0.0090 0.0000 -0.0023 -0.0319 0.267 - 71 1.9146 3.5155 1.1831 0.5047 0.0695 0.1871 0.1433 0.0091 0.0000 -0.0019 -0.0326 0.263 - 72 2.2558 3.3805 1.1921 0.5038 0.0655 0.1943 0.1488 0.0092 0.0000 -0.0015 -0.0335 0.260 - 73 2.6109 3.2400 1.1821 0.5032 0.0622 0.2024 0.1551 0.0093 0.0000 -0.0012 -0.0346 0.258 - 74 2.9762 3.0955 1.1548 0.5020 0.0597 0.2114 0.1620 0.0095 0.0000 -0.0009 -0.0358 0.255 - 75 3.3476 2.9485 1.1122 0.5004 0.0578 0.2213 0.1695 0.0096 0.0000 -0.0005 -0.0371 0.253 - 76 3.7210 2.8008 1.0564 0.4978 0.0563 0.2318 0.1775 0.0098 0.0000 -0.0001 -0.0385 0.251 - 77 4.0924 2.6538 0.9900 0.4934 0.0554 0.2425 0.1858 0.0099 0.0000 0.0003 -0.0399 0.248 - 78 4.4577 2.5093 0.9155 0.4869 0.0549 0.2532 0.1939 0.0099 0.0000 0.0009 -0.0412 0.246 - 79 4.8128 2.3687 0.8353 0.4773 0.0548 0.2630 0.2014 0.0098 0.0000 0.0015 -0.0423 0.242 - 80 5.1540 2.2338 0.7518 0.4644 0.0552 0.2713 0.2078 0.0097 0.0000 0.0023 -0.0430 0.239 - 81 5.4774 2.1058 0.6671 0.4475 0.0561 0.2774 0.2125 0.0095 0.0000 0.0033 -0.0432 0.234 - 82 5.7795 1.9862 0.5830 0.4260 0.0574 0.2800 0.2145 0.0090 0.0000 0.0046 -0.0425 0.229 - 83 6.0570 1.8764 0.5012 0.3998 0.0591 0.2783 0.2131 0.0085 0.0000 0.0062 -0.0409 0.221 - 84 6.3069 1.7776 0.4225 0.3682 0.0611 0.2706 0.2073 0.0079 0.0000 0.0080 -0.0381 0.211 - 85 6.5264 1.6907 0.3478 0.3313 0.0632 0.2560 0.1961 0.0069 0.0000 0.0100 -0.0340 0.199 - 86 6.7314 1.6096 0.3326 0.2869 0.0654 0.2329 0.1784 0.0059 0.0000 0.0118 -0.0286 0.184 - 87 6.9144 1.5372 0.2507 0.2321 0.0674 0.1974 0.1512 0.0044 0.0000 0.0130 -0.0218 0.164 - 88 7.0535 1.4822 0.1746 0.1707 0.0691 0.1506 0.1154 0.0028 0.0000 0.0123 -0.0146 0.144 - 89 7.1471 1.4451 0.1029 0.1045 0.0702 0.0946 0.0725 0.0013 0.0000 0.0090 -0.0081 0.126 - 90 7.1941 1.4265 0.0340 0.0352 0.0708 0.0324 0.0248 -0.0003 0.0000 0.0033 -0.0025 0.115 + 61 0.0047 4.2713 0.0803 0.5502 0.0905 0.1644 0.1259 0.0386 0.0000 -0.0075 -0.0341 0.310 + 62 0.0418 4.2566 0.2392 0.5074 0.0907 0.1549 0.1187 0.0111 0.0000 -0.0074 -0.0319 0.312 + 63 0.1156 4.2274 0.3930 0.5043 0.0906 0.1553 0.1189 0.0094 0.0000 -0.0070 -0.0317 0.309 + 64 0.2254 4.1839 0.5386 0.5036 0.0902 0.1567 0.1200 0.0090 0.0000 -0.0064 -0.0314 0.303 + 65 0.3698 4.1268 0.6730 0.5037 0.0893 0.1589 0.1217 0.0089 0.0000 -0.0056 -0.0311 0.296 + 66 0.5474 4.0565 0.7936 0.5036 0.0878 0.1617 0.1239 0.0088 0.0000 -0.0049 -0.0309 0.289 + 67 0.7617 3.9717 0.9441 0.5035 0.0854 0.1651 0.1265 0.0088 0.0000 -0.0041 -0.0308 0.282 + 68 1.0116 3.8728 1.0344 0.5029 0.0823 0.1692 0.1296 0.0087 0.0000 -0.0034 -0.0309 0.276 + 69 1.2891 3.7630 1.1046 0.5025 0.0784 0.1740 0.1333 0.0088 0.0000 -0.0028 -0.0312 0.271 + 70 1.5912 3.6435 1.1542 0.5018 0.0740 0.1795 0.1375 0.0089 0.0000 -0.0023 -0.0317 0.267 + 71 1.9146 3.5155 1.1831 0.5011 0.0696 0.1858 0.1423 0.0090 0.0000 -0.0019 -0.0324 0.263 + 72 2.2558 3.3805 1.1921 0.5004 0.0656 0.1929 0.1478 0.0092 0.0000 -0.0015 -0.0333 0.260 + 73 2.6109 3.2400 1.1821 0.4999 0.0623 0.2011 0.1541 0.0093 0.0000 -0.0012 -0.0344 0.258 + 74 2.9762 3.0955 1.1548 0.4992 0.0598 0.2103 0.1610 0.0095 0.0000 -0.0009 -0.0356 0.255 + 75 3.3476 2.9485 1.1122 0.4978 0.0579 0.2202 0.1686 0.0096 0.0000 -0.0005 -0.0369 0.253 + 76 3.7210 2.8008 1.0564 0.4954 0.0564 0.2307 0.1767 0.0098 0.0000 -0.0001 -0.0384 0.251 + 77 4.0924 2.6538 0.9900 0.4914 0.0555 0.2415 0.1850 0.0098 0.0000 0.0003 -0.0398 0.248 + 78 4.4577 2.5093 0.9155 0.4851 0.0549 0.2522 0.1932 0.0098 0.0000 0.0008 -0.0411 0.246 + 79 4.8128 2.3687 0.8353 0.4759 0.0549 0.2621 0.2008 0.0098 0.0000 0.0015 -0.0422 0.243 + 80 5.1540 2.2338 0.7518 0.4632 0.0552 0.2706 0.2073 0.0097 0.0000 0.0023 -0.0429 0.239 + 81 5.4774 2.1058 0.6671 0.4464 0.0561 0.2767 0.2120 0.0095 0.0000 0.0033 -0.0430 0.234 + 82 5.7795 1.9862 0.5830 0.4251 0.0574 0.2795 0.2141 0.0090 0.0000 0.0046 -0.0424 0.229 + 83 6.0570 1.8764 0.5012 0.3991 0.0591 0.2777 0.2127 0.0085 0.0000 0.0062 -0.0408 0.221 + 84 6.3069 1.7776 0.4225 0.3677 0.0611 0.2702 0.2070 0.0079 0.0000 0.0080 -0.0380 0.211 + 85 6.5264 1.6907 0.3478 0.3309 0.0632 0.2557 0.1959 0.0069 0.0000 0.0100 -0.0340 0.199 + 86 6.7314 1.6096 0.3326 0.2865 0.0654 0.2326 0.1782 0.0059 0.0000 0.0118 -0.0286 0.184 + 87 6.9144 1.5372 0.2507 0.2318 0.0674 0.1971 0.1510 0.0044 0.0000 0.0130 -0.0218 0.164 + 88 7.0535 1.4822 0.1746 0.1706 0.0691 0.1505 0.1153 0.0028 0.0000 0.0123 -0.0146 0.144 + 89 7.1471 1.4451 0.1029 0.1044 0.0702 0.0945 0.0724 0.0013 0.0000 0.0090 -0.0081 0.125 + 90 7.1941 1.4265 0.0340 0.0351 0.0709 0.0323 0.0248 -0.0003 0.0000 0.0033 -0.0025 0.115 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02635 Clsurf = 0.00282 - CYsurf = 0.00418 Cmsurf = -0.12887 - CDsurf = 0.00152 Cnsurf = -0.00238 - CDisurf = 0.00152 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02621 Clsurf = 0.00281 + CYsurf = 0.00416 Cmsurf = -0.12823 + CDsurf = 0.00151 Cnsurf = -0.00237 + CDisurf = 0.00151 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16056 CDsurf = 0.00912 + CLsurf = 0.15974 CDsurf = 0.00909 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.5550 0.0904 0.1658 0.1270 0.0391 0.0000 -0.0075 0.0343 0.309 - 92 -0.0418 4.2566 0.2392 0.5115 0.0906 0.1562 0.1196 0.0112 0.0000 -0.0074 0.0322 0.312 - 93 -0.1156 4.2274 0.3930 0.5085 0.0906 0.1565 0.1199 0.0094 0.0000 -0.0071 0.0319 0.309 - 94 -0.2254 4.1839 0.5386 0.5077 0.0901 0.1580 0.1210 0.0090 0.0000 -0.0064 0.0316 0.303 - 95 -0.3698 4.1268 0.6730 0.5077 0.0892 0.1602 0.1227 0.0089 0.0000 -0.0057 0.0313 0.296 - 96 -0.5474 4.0565 0.7936 0.5078 0.0877 0.1630 0.1249 0.0088 0.0000 -0.0049 0.0311 0.289 - 97 -0.7617 3.9717 0.9441 0.5073 0.0854 0.1664 0.1274 0.0088 0.0000 -0.0041 0.0310 0.282 - 98 -1.0116 3.8728 1.0344 0.5070 0.0822 0.1706 0.1306 0.0088 0.0000 -0.0034 0.0311 0.276 - 99 -1.2891 3.7630 1.1046 0.5061 0.0782 0.1752 0.1342 0.0089 0.0000 -0.0028 0.0314 0.271 - 100 -1.5912 3.6435 1.1542 0.5056 0.0739 0.1808 0.1385 0.0090 0.0000 -0.0023 0.0319 0.267 - 101 -1.9146 3.5155 1.1831 0.5047 0.0695 0.1871 0.1433 0.0091 0.0000 -0.0019 0.0326 0.263 - 102 -2.2558 3.3805 1.1921 0.5038 0.0655 0.1943 0.1488 0.0092 0.0000 -0.0015 0.0335 0.260 - 103 -2.6109 3.2400 1.1821 0.5031 0.0622 0.2024 0.1551 0.0093 0.0000 -0.0012 0.0346 0.258 - 104 -2.9762 3.0955 1.1548 0.5020 0.0597 0.2114 0.1620 0.0095 0.0000 -0.0009 0.0358 0.255 - 105 -3.3476 2.9485 1.1122 0.5004 0.0578 0.2213 0.1695 0.0096 0.0000 -0.0005 0.0371 0.253 - 106 -3.7210 2.8008 1.0564 0.4978 0.0563 0.2318 0.1775 0.0098 0.0000 -0.0001 0.0385 0.251 - 107 -4.0924 2.6538 0.9900 0.4934 0.0554 0.2425 0.1858 0.0099 0.0000 0.0003 0.0399 0.248 - 108 -4.4577 2.5093 0.9155 0.4869 0.0549 0.2532 0.1939 0.0099 0.0000 0.0009 0.0412 0.246 - 109 -4.8128 2.3687 0.8353 0.4773 0.0548 0.2629 0.2014 0.0098 0.0000 0.0015 0.0423 0.242 - 110 -5.1540 2.2338 0.7518 0.4644 0.0552 0.2713 0.2078 0.0097 0.0000 0.0023 0.0430 0.239 - 111 -5.4774 2.1058 0.6671 0.4475 0.0561 0.2774 0.2125 0.0095 0.0000 0.0033 0.0432 0.234 - 112 -5.7795 1.9862 0.5830 0.4260 0.0574 0.2800 0.2145 0.0090 0.0000 0.0046 0.0425 0.229 - 113 -6.0570 1.8764 0.5012 0.3998 0.0591 0.2783 0.2131 0.0085 0.0000 0.0062 0.0409 0.221 - 114 -6.3069 1.7776 0.4225 0.3682 0.0611 0.2706 0.2072 0.0079 0.0000 0.0080 0.0381 0.211 - 115 -6.5264 1.6907 0.3478 0.3313 0.0632 0.2560 0.1961 0.0069 0.0000 0.0100 0.0340 0.199 - 116 -6.7314 1.6096 0.3326 0.2869 0.0654 0.2329 0.1784 0.0059 0.0000 0.0118 0.0286 0.184 - 117 -6.9144 1.5372 0.2507 0.2321 0.0674 0.1974 0.1512 0.0044 0.0000 0.0130 0.0218 0.164 - 118 -7.0535 1.4822 0.1746 0.1707 0.0691 0.1506 0.1154 0.0028 0.0000 0.0123 0.0146 0.144 - 119 -7.1471 1.4451 0.1029 0.1045 0.0702 0.0946 0.0725 0.0013 0.0000 0.0090 0.0081 0.126 - 120 -7.1941 1.4265 0.0340 0.0352 0.0708 0.0324 0.0248 -0.0003 0.0000 0.0033 0.0025 0.115 + 91 -0.0047 4.2713 0.0803 0.5502 0.0905 0.1644 0.1259 0.0386 0.0000 -0.0075 0.0341 0.310 + 92 -0.0418 4.2566 0.2392 0.5074 0.0907 0.1549 0.1187 0.0111 0.0000 -0.0074 0.0319 0.312 + 93 -0.1156 4.2274 0.3930 0.5043 0.0906 0.1553 0.1189 0.0094 0.0000 -0.0070 0.0317 0.309 + 94 -0.2254 4.1839 0.5386 0.5036 0.0902 0.1567 0.1200 0.0090 0.0000 -0.0064 0.0314 0.303 + 95 -0.3698 4.1268 0.6730 0.5037 0.0893 0.1589 0.1217 0.0089 0.0000 -0.0056 0.0311 0.296 + 96 -0.5474 4.0565 0.7936 0.5036 0.0878 0.1617 0.1239 0.0088 0.0000 -0.0049 0.0309 0.289 + 97 -0.7617 3.9717 0.9441 0.5035 0.0854 0.1651 0.1265 0.0088 0.0000 -0.0041 0.0308 0.282 + 98 -1.0116 3.8728 1.0344 0.5029 0.0823 0.1692 0.1296 0.0087 0.0000 -0.0034 0.0309 0.276 + 99 -1.2891 3.7630 1.1046 0.5025 0.0784 0.1740 0.1333 0.0088 0.0000 -0.0028 0.0312 0.271 + 100 -1.5912 3.6435 1.1542 0.5018 0.0740 0.1795 0.1375 0.0089 0.0000 -0.0023 0.0317 0.267 + 101 -1.9146 3.5155 1.1831 0.5011 0.0696 0.1858 0.1423 0.0090 0.0000 -0.0019 0.0324 0.263 + 102 -2.2558 3.3805 1.1921 0.5004 0.0656 0.1929 0.1478 0.0092 0.0000 -0.0015 0.0333 0.260 + 103 -2.6109 3.2400 1.1821 0.4999 0.0623 0.2011 0.1541 0.0093 0.0000 -0.0012 0.0344 0.258 + 104 -2.9762 3.0955 1.1548 0.4992 0.0598 0.2103 0.1610 0.0095 0.0000 -0.0009 0.0356 0.255 + 105 -3.3476 2.9485 1.1122 0.4978 0.0579 0.2202 0.1686 0.0096 0.0000 -0.0005 0.0369 0.253 + 106 -3.7210 2.8008 1.0564 0.4954 0.0564 0.2307 0.1767 0.0098 0.0000 -0.0001 0.0384 0.251 + 107 -4.0924 2.6538 0.9900 0.4914 0.0555 0.2415 0.1850 0.0098 0.0000 0.0003 0.0398 0.248 + 108 -4.4577 2.5093 0.9155 0.4851 0.0549 0.2522 0.1932 0.0098 0.0000 0.0008 0.0411 0.246 + 109 -4.8128 2.3687 0.8353 0.4759 0.0549 0.2621 0.2008 0.0098 0.0000 0.0015 0.0422 0.243 + 110 -5.1540 2.2338 0.7518 0.4632 0.0552 0.2706 0.2073 0.0097 0.0000 0.0023 0.0429 0.239 + 111 -5.4774 2.1058 0.6671 0.4464 0.0561 0.2767 0.2120 0.0095 0.0000 0.0033 0.0430 0.234 + 112 -5.7795 1.9862 0.5830 0.4251 0.0574 0.2795 0.2141 0.0090 0.0000 0.0046 0.0424 0.229 + 113 -6.0570 1.8764 0.5012 0.3991 0.0591 0.2777 0.2127 0.0085 0.0000 0.0062 0.0408 0.221 + 114 -6.3069 1.7776 0.4225 0.3677 0.0611 0.2702 0.2070 0.0079 0.0000 0.0080 0.0380 0.211 + 115 -6.5264 1.6907 0.3478 0.3309 0.0632 0.2557 0.1959 0.0069 0.0000 0.0100 0.0340 0.199 + 116 -6.7314 1.6096 0.3326 0.2865 0.0654 0.2326 0.1782 0.0059 0.0000 0.0118 0.0286 0.184 + 117 -6.9144 1.5372 0.2507 0.2318 0.0674 0.1971 0.1510 0.0044 0.0000 0.0130 0.0218 0.164 + 118 -7.0535 1.4822 0.1746 0.1706 0.0691 0.1505 0.1153 0.0028 0.0000 0.0123 0.0146 0.144 + 119 -7.1471 1.4451 0.1029 0.1044 0.0702 0.0945 0.0724 0.0013 0.0000 0.0090 0.0081 0.125 + 120 -7.1941 1.4265 0.0340 0.0351 0.0709 0.0323 0.0248 -0.0003 0.0000 0.0033 0.0025 0.115 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.347 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.358 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.367 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.373 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.379 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.381 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.372 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.360 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.341 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.305 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.324 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.335 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.344 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.344 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.361 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.357 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.358 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.343 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.334 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.304 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.271 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.266 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.256 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.251 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.248 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.245 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.256 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.247 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.242 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.219 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.210 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.202 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.186 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.167 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.146 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.128 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.118 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.200 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.182 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.166 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.139 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.127 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.109 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00636 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.04671 + CLsurf = 0.00629 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = 0.04679 CDsurf = -0.00023 Cnsurf = -0.00000 CDisurf = -0.00023 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00642 CDsurf = -0.00023 + CLsurf = 0.00635 CDsurf = -0.00023 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.1397 0.1265 0.0630 0.0054 -0.0019 0.0000 0.0036 0.0003 -0.419 - 152 -1.3090 31.2096 11.6724 0.2031 0.1377 0.0252 0.0066 -0.0007 0.0000 0.0044 0.0007 -0.420 - 153 -0.9350 34.0626 12.7394 0.2260 0.1312 0.0161 0.0067 -0.0002 0.0000 0.0051 0.0012 -0.518 - 154 -0.5610 36.1619 13.5246 0.2393 0.1299 0.0111 0.0066 0.0002 0.0000 0.0055 0.0017 -0.574 - 155 -0.1870 37.5332 14.0374 0.2468 0.1309 0.0076 0.0065 0.0008 0.0000 0.0055 0.0027 -0.597 - 156 0.1870 37.5332 14.0374 0.2468 0.1309 0.0076 0.0065 0.0008 0.0000 0.0055 0.0027 -0.597 - 157 0.5610 36.1619 13.5246 0.2393 0.1299 0.0111 0.0066 0.0002 0.0000 0.0055 0.0017 -0.574 - 158 0.9350 34.0626 12.7394 0.2260 0.1312 0.0161 0.0067 -0.0002 0.0000 0.0051 0.0012 -0.518 - 159 1.3090 31.2096 11.6724 0.2031 0.1377 0.0252 0.0066 -0.0007 0.0000 0.0044 0.0007 -0.420 - 160 1.6830 26.5957 9.9468 0.1397 0.1265 0.0630 0.0054 -0.0019 0.0000 0.0036 0.0003 -0.419 + 151 -1.6830 26.5957 9.9468 0.1380 0.1265 0.0622 0.0054 -0.0019 0.0000 0.0037 0.0003 -0.432 + 152 -1.3090 31.2096 11.6724 0.2007 0.1377 0.0249 0.0065 -0.0007 0.0000 0.0044 0.0007 -0.431 + 153 -0.9350 34.0626 12.7394 0.2235 0.1313 0.0160 0.0066 -0.0002 0.0000 0.0051 0.0012 -0.530 + 154 -0.5610 36.1619 13.5246 0.2367 0.1301 0.0110 0.0066 0.0002 0.0000 0.0055 0.0017 -0.586 + 155 -0.1870 37.5332 14.0374 0.2442 0.1312 0.0075 0.0065 0.0008 0.0000 0.0055 0.0027 -0.609 + 156 0.1870 37.5332 14.0374 0.2442 0.1312 0.0075 0.0065 0.0008 0.0000 0.0055 0.0027 -0.609 + 157 0.5610 36.1619 13.5246 0.2367 0.1301 0.0110 0.0066 0.0002 0.0000 0.0055 0.0017 -0.586 + 158 0.9350 34.0626 12.7394 0.2235 0.1313 0.0160 0.0066 -0.0002 0.0000 0.0051 0.0012 -0.530 + 159 1.3090 31.2096 11.6724 0.2007 0.1377 0.0249 0.0065 -0.0007 0.0000 0.0044 0.0007 -0.431 + 160 1.6830 26.5957 9.9468 0.1380 0.1265 0.0622 0.0054 -0.0019 0.0000 0.0037 0.0003 -0.432 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00000 Clsurf = -0.00000 + CLsurf = -0.00000 Clsurf = -0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = 0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 -0.535 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.304 - 163 0.0000 34.0626 12.7394 -0.0000 0.0001 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.044 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.101 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.427 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.499 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.553 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.605 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.687 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 0.073 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.497 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.021 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.140 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.270 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.455 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.541 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.578 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.619 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.684 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_03_05.txt b/regression/scripts/AVL/avl_files/strip_forces_case_03_05.txt index 0e72e36502..db5ae3c956 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_03_05.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_03_05.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.38075 Clsurf = -0.07408 - CYsurf = -0.02078 Cmsurf = -0.34172 - CDsurf = 0.01291 Cnsurf = -0.00702 - CDisurf = 0.01291 CDvsurf = 0.00000 + CLsurf = 0.38143 Clsurf = -0.07415 + CYsurf = -0.02053 Cmsurf = -0.34203 + CDsurf = 0.01251 Cnsurf = -0.00705 + CDisurf = 0.01251 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.74422 CDsurf = 0.02520 + CLsurf = 0.74551 CDsurf = 0.02441 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 4.9118 0.1741 0.7286 0.5643 0.6020 0.0000 -0.0323 -0.1566 0.307 - 2 0.1025 7.6885 1.0492 4.5026 0.1738 0.7428 0.5753 0.1194 0.0000 -0.0325 -0.1471 0.307 - 3 0.2837 7.5620 1.7073 4.4671 0.1724 0.7542 0.5842 0.0894 0.0000 -0.0302 -0.1462 0.302 - 4 0.5530 7.3741 2.3052 4.4460 0.1695 0.7716 0.5977 0.0796 0.0000 -0.0266 -0.1458 0.295 - 5 0.9075 7.1267 2.8223 4.4106 0.1636 0.7938 0.6148 0.0706 0.0000 -0.0227 -0.1460 0.287 - 6 1.3432 6.8226 3.2414 4.3540 0.1509 0.8200 0.6351 0.0639 0.0000 -0.0192 -0.1471 0.280 - 7 1.8554 6.4651 3.5491 4.2706 0.1255 0.8501 0.6584 0.0576 0.0000 -0.0164 -0.1495 0.275 - 8 2.4386 6.0582 3.7368 4.1417 0.1001 0.8823 0.6834 0.0439 0.0000 -0.0150 -0.1530 0.272 - 9 3.0862 5.6062 3.8005 3.9839 0.0865 0.9186 0.7114 0.0367 0.0000 -0.0145 -0.1582 0.270 - 10 3.7613 5.1351 3.4440 3.7948 0.0746 0.9574 0.7415 0.0247 0.0000 -0.0157 -0.1650 0.271 - 11 4.4532 4.6522 3.3149 3.5919 0.0605 1.0019 0.7760 0.0155 0.0000 -0.0180 -0.1737 0.273 - 12 5.1831 4.1429 3.0930 3.3604 0.0390 1.0549 0.8170 0.0018 0.0000 -0.0205 -0.1838 0.275 - 13 6.0123 3.7903 3.4706 3.1304 0.0245 1.0219 0.8326 -0.0044 0.0000 -0.0185 -0.2031 0.272 - 14 6.9353 3.6075 3.3775 2.9503 0.0227 1.0116 0.8242 -0.0019 0.0000 -0.0187 -0.2015 0.273 - 15 7.8737 3.4215 3.2389 2.7875 0.0192 1.0077 0.8210 -0.0016 0.0000 -0.0186 -0.2007 0.273 - 16 8.8172 3.2345 3.0619 2.6341 0.0169 1.0073 0.8207 -0.0019 0.0000 -0.0184 -0.2004 0.272 - 17 9.7556 3.0486 2.8543 2.4845 0.0165 1.0081 0.8214 -0.0024 0.0000 -0.0181 -0.2004 0.272 - 18 10.6786 2.8657 2.6240 2.3385 0.0174 1.0096 0.8225 -0.0030 0.0000 -0.0178 -0.2004 0.272 - 19 11.5760 2.6879 2.3787 2.1951 0.0192 1.0104 0.8232 -0.0035 0.0000 -0.0174 -0.2001 0.271 - 20 12.4328 2.5181 2.1010 2.0537 0.0217 1.0092 0.8222 -0.0041 0.0000 -0.0168 -0.1994 0.270 - 21 13.2400 2.3582 1.8520 1.9134 0.0254 1.0040 0.8180 -0.0044 0.0000 -0.0159 -0.1976 0.269 - 22 13.9941 2.2087 1.6074 1.7715 0.0305 0.9925 0.8086 -0.0046 0.0000 -0.0145 -0.1942 0.268 - 23 14.6868 2.0715 1.3716 1.6243 0.0375 0.9703 0.7906 -0.0045 0.0000 -0.0122 -0.1881 0.265 - 24 15.3105 1.9479 1.1479 1.4661 0.0464 0.9313 0.7588 -0.0039 0.0000 -0.0088 -0.1780 0.262 - 25 15.8583 1.8393 0.9381 1.2884 0.0565 0.8665 0.7060 -0.0022 0.0000 -0.0053 -0.1632 0.258 - 26 16.3244 1.7470 0.7427 1.0851 0.0669 0.7675 0.6253 0.0041 0.0000 -0.0068 -0.1465 0.261 - 27 16.6722 1.4928 0.4131 0.8648 0.0779 1.9587 0.5863 -0.0210 0.0000 -0.0089 -0.0764 0.265 - 28 16.9098 1.1466 0.2292 0.6407 0.0930 1.9007 0.5689 -0.0478 0.0000 0.0140 -0.0634 0.225 - 29 17.0696 0.9138 0.1104 0.3958 0.1054 1.4867 0.4450 -0.0686 0.0000 0.0358 -0.0378 0.170 - 30 17.1499 0.7967 0.0322 0.1340 0.1118 0.5877 0.1759 -0.0513 0.0000 0.0234 -0.0104 0.117 + 1 0.0114 7.7520 0.3539 4.9295 0.1742 0.7315 0.5665 0.6026 0.0000 -0.0338 -0.1583 0.310 + 2 0.1025 7.6885 1.0491 4.5181 0.1739 0.7454 0.5774 0.1194 0.0000 -0.0338 -0.1485 0.309 + 3 0.2837 7.5620 1.7073 4.4825 0.1727 0.7570 0.5863 0.0889 0.0000 -0.0315 -0.1477 0.304 + 4 0.5530 7.3741 2.3052 4.4596 0.1700 0.7744 0.5998 0.0771 0.0000 -0.0279 -0.1473 0.297 + 5 0.9075 7.1267 2.8223 4.4257 0.1642 0.7966 0.6170 0.0707 0.0000 -0.0241 -0.1475 0.289 + 6 1.3432 6.8226 3.2414 4.3666 0.1515 0.8228 0.6373 0.0610 0.0000 -0.0206 -0.1486 0.282 + 7 1.8554 6.4651 3.5491 4.2776 0.1261 0.8530 0.6607 0.0482 0.0000 -0.0178 -0.1508 0.277 + 8 2.4386 6.0582 3.7368 4.1567 0.1007 0.8855 0.6858 0.0444 0.0000 -0.0160 -0.1543 0.273 + 9 3.0862 5.6062 3.8005 3.9969 0.0873 0.9217 0.7139 0.0361 0.0000 -0.0154 -0.1594 0.272 + 10 3.7613 5.1351 3.4440 3.8000 0.0752 0.9583 0.7422 0.0275 0.0000 -0.0165 -0.1659 0.272 + 11 4.4532 4.6522 3.3149 3.6118 0.0605 1.0077 0.7805 0.0141 0.0000 -0.0169 -0.1737 0.272 + 12 5.1831 4.1429 3.0930 3.3639 0.0384 1.0563 0.8181 0.0002 0.0000 -0.0194 -0.1831 0.274 + 13 6.0123 3.7903 3.4706 3.1333 0.0240 1.0229 0.8334 -0.0043 0.0000 -0.0170 -0.2020 0.270 + 14 6.9353 3.6075 3.3775 2.9519 0.0225 1.0122 0.8247 -0.0019 0.0000 -0.0172 -0.2003 0.271 + 15 7.8737 3.4215 3.2389 2.7890 0.0190 1.0082 0.8215 -0.0016 0.0000 -0.0170 -0.1994 0.271 + 16 8.8172 3.2345 3.0619 2.6356 0.0168 1.0079 0.8212 -0.0020 0.0000 -0.0168 -0.1991 0.270 + 17 9.7556 3.0486 2.8543 2.4858 0.0164 1.0087 0.8218 -0.0025 0.0000 -0.0165 -0.1991 0.270 + 18 10.6786 2.8657 2.6239 2.3396 0.0173 1.0100 0.8229 -0.0030 0.0000 -0.0162 -0.1990 0.270 + 19 11.5760 2.6879 2.3787 2.1960 0.0191 1.0108 0.8236 -0.0036 0.0000 -0.0158 -0.1988 0.269 + 20 12.4328 2.5181 2.1010 2.0545 0.0217 1.0095 0.8225 -0.0041 0.0000 -0.0152 -0.1980 0.269 + 21 13.2400 2.3582 1.8520 1.9140 0.0253 1.0044 0.8183 -0.0045 0.0000 -0.0143 -0.1963 0.267 + 22 13.9941 2.2087 1.6074 1.7721 0.0304 0.9928 0.8089 -0.0047 0.0000 -0.0128 -0.1928 0.266 + 23 14.6868 2.0715 1.3716 1.6247 0.0374 0.9706 0.7908 -0.0045 0.0000 -0.0105 -0.1867 0.263 + 24 15.3105 1.9479 1.1479 1.4662 0.0464 0.9314 0.7589 -0.0040 0.0000 -0.0072 -0.1766 0.259 + 25 15.8583 1.8393 0.9381 1.2884 0.0565 0.8665 0.7060 -0.0023 0.0000 -0.0037 -0.1617 0.255 + 26 16.3244 1.7470 0.7427 1.0847 0.0666 0.7672 0.6251 0.0040 0.0000 -0.0052 -0.1451 0.258 + 27 16.6722 1.4928 0.4131 0.8643 0.0776 1.9578 0.5860 -0.0213 0.0000 -0.0076 -0.0758 0.263 + 28 16.9098 1.1466 0.2292 0.6405 0.0930 1.9003 0.5688 -0.0481 0.0000 0.0150 -0.0629 0.224 + 29 17.0696 0.9138 0.1104 0.3958 0.1055 1.4868 0.4451 -0.0689 0.0000 0.0364 -0.0375 0.168 + 30 17.1499 0.7967 0.0322 0.1341 0.1125 0.5881 0.1760 -0.0517 0.0000 0.0235 -0.0103 0.116 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.38075 Clsurf = 0.07408 - CYsurf = 0.02078 Cmsurf = -0.34171 - CDsurf = 0.01291 Cnsurf = 0.00702 - CDisurf = 0.01291 CDvsurf = 0.00000 + CLsurf = 0.38143 Clsurf = 0.07415 + CYsurf = 0.02053 Cmsurf = -0.34203 + CDsurf = 0.01251 Cnsurf = 0.00705 + CDisurf = 0.01251 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.74422 CDsurf = 0.02520 + CLsurf = 0.74551 CDsurf = 0.02441 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 4.9118 0.1743 0.7286 0.5643 0.6020 0.0000 -0.0323 0.1566 0.307 - 32 -0.1025 7.6885 1.0492 4.5026 0.1738 0.7428 0.5753 0.1194 0.0000 -0.0325 0.1471 0.307 - 33 -0.2837 7.5620 1.7073 4.4671 0.1724 0.7542 0.5842 0.0894 0.0000 -0.0302 0.1462 0.302 - 34 -0.5530 7.3741 2.3052 4.4460 0.1695 0.7716 0.5977 0.0796 0.0000 -0.0266 0.1458 0.295 - 35 -0.9075 7.1267 2.8223 4.4106 0.1636 0.7938 0.6148 0.0706 0.0000 -0.0227 0.1460 0.287 - 36 -1.3432 6.8226 3.2414 4.3540 0.1509 0.8200 0.6351 0.0639 0.0000 -0.0192 0.1471 0.280 - 37 -1.8554 6.4651 3.5491 4.2706 0.1255 0.8501 0.6584 0.0576 0.0000 -0.0164 0.1495 0.275 - 38 -2.4386 6.0582 3.7368 4.1417 0.1001 0.8823 0.6834 0.0439 0.0000 -0.0150 0.1530 0.272 - 39 -3.0862 5.6062 3.8005 3.9839 0.0865 0.9186 0.7114 0.0367 0.0000 -0.0145 0.1582 0.270 - 40 -3.7613 5.1351 3.4440 3.7948 0.0746 0.9574 0.7415 0.0246 0.0000 -0.0157 0.1650 0.271 - 41 -4.4532 4.6522 3.3149 3.5919 0.0605 1.0019 0.7760 0.0155 0.0000 -0.0180 0.1737 0.273 - 42 -5.1831 4.1429 3.0930 3.3604 0.0390 1.0549 0.8170 0.0018 0.0000 -0.0205 0.1838 0.275 - 43 -6.0123 3.7903 3.4706 3.1304 0.0245 1.0219 0.8326 -0.0044 0.0000 -0.0185 0.2031 0.272 - 44 -6.9353 3.6075 3.3775 2.9503 0.0227 1.0116 0.8242 -0.0019 0.0000 -0.0187 0.2015 0.273 - 45 -7.8737 3.4215 3.2389 2.7875 0.0192 1.0077 0.8210 -0.0016 0.0000 -0.0186 0.2007 0.273 - 46 -8.8172 3.2345 3.0619 2.6341 0.0169 1.0073 0.8207 -0.0019 0.0000 -0.0184 0.2004 0.272 - 47 -9.7556 3.0486 2.8543 2.4844 0.0165 1.0081 0.8214 -0.0024 0.0000 -0.0181 0.2004 0.272 - 48 -10.6786 2.8657 2.6240 2.3385 0.0174 1.0096 0.8225 -0.0030 0.0000 -0.0178 0.2004 0.272 - 49 -11.5760 2.6879 2.3787 2.1951 0.0192 1.0104 0.8232 -0.0035 0.0000 -0.0174 0.2001 0.271 - 50 -12.4328 2.5181 2.1010 2.0537 0.0217 1.0091 0.8222 -0.0041 0.0000 -0.0168 0.1994 0.270 - 51 -13.2400 2.3582 1.8520 1.9134 0.0254 1.0040 0.8180 -0.0044 0.0000 -0.0159 0.1976 0.269 - 52 -13.9941 2.2087 1.6074 1.7715 0.0305 0.9925 0.8086 -0.0046 0.0000 -0.0145 0.1942 0.268 - 53 -14.6868 2.0715 1.3716 1.6243 0.0375 0.9703 0.7906 -0.0045 0.0000 -0.0122 0.1881 0.265 - 54 -15.3105 1.9479 1.1479 1.4661 0.0464 0.9313 0.7588 -0.0039 0.0000 -0.0088 0.1780 0.262 - 55 -15.8583 1.8393 0.9381 1.2884 0.0565 0.8665 0.7060 -0.0022 0.0000 -0.0053 0.1632 0.258 - 56 -16.3244 1.7470 0.7427 1.0851 0.0669 0.7675 0.6253 0.0041 0.0000 -0.0068 0.1465 0.261 - 57 -16.6722 1.4928 0.4131 0.8648 0.0779 1.9587 0.5863 -0.0210 0.0000 -0.0089 0.0764 0.265 - 58 -16.9098 1.1466 0.2292 0.6407 0.0930 1.9006 0.5689 -0.0478 0.0000 0.0140 0.0634 0.225 - 59 -17.0696 0.9138 0.1104 0.3958 0.1054 1.4867 0.4450 -0.0686 0.0000 0.0358 0.0378 0.170 - 60 -17.1499 0.7967 0.0322 0.1340 0.1118 0.5877 0.1759 -0.0513 0.0000 0.0234 0.0104 0.117 + 31 -0.0114 7.7520 0.3539 4.9295 0.1742 0.7315 0.5665 0.6026 0.0000 -0.0338 0.1583 0.310 + 32 -0.1025 7.6885 1.0491 4.5181 0.1739 0.7454 0.5774 0.1194 0.0000 -0.0338 0.1485 0.309 + 33 -0.2837 7.5620 1.7073 4.4825 0.1727 0.7570 0.5863 0.0889 0.0000 -0.0315 0.1477 0.304 + 34 -0.5530 7.3741 2.3052 4.4596 0.1700 0.7744 0.5998 0.0771 0.0000 -0.0279 0.1473 0.297 + 35 -0.9075 7.1267 2.8223 4.4257 0.1642 0.7966 0.6170 0.0707 0.0000 -0.0241 0.1475 0.289 + 36 -1.3432 6.8226 3.2414 4.3666 0.1515 0.8228 0.6373 0.0610 0.0000 -0.0206 0.1486 0.282 + 37 -1.8554 6.4651 3.5491 4.2776 0.1261 0.8530 0.6607 0.0482 0.0000 -0.0178 0.1508 0.277 + 38 -2.4386 6.0582 3.7368 4.1567 0.1007 0.8855 0.6858 0.0444 0.0000 -0.0160 0.1543 0.273 + 39 -3.0862 5.6062 3.8005 3.9969 0.0873 0.9217 0.7139 0.0361 0.0000 -0.0154 0.1594 0.272 + 40 -3.7613 5.1351 3.4440 3.8000 0.0752 0.9583 0.7422 0.0275 0.0000 -0.0165 0.1659 0.272 + 41 -4.4532 4.6522 3.3149 3.6118 0.0605 1.0077 0.7805 0.0141 0.0000 -0.0169 0.1737 0.272 + 42 -5.1831 4.1429 3.0930 3.3639 0.0384 1.0563 0.8181 0.0002 0.0000 -0.0194 0.1831 0.274 + 43 -6.0123 3.7903 3.4706 3.1333 0.0240 1.0229 0.8334 -0.0043 0.0000 -0.0170 0.2020 0.270 + 44 -6.9353 3.6075 3.3775 2.9519 0.0225 1.0122 0.8247 -0.0019 0.0000 -0.0172 0.2003 0.271 + 45 -7.8737 3.4215 3.2389 2.7890 0.0190 1.0082 0.8215 -0.0016 0.0000 -0.0170 0.1994 0.271 + 46 -8.8172 3.2345 3.0619 2.6356 0.0168 1.0079 0.8212 -0.0020 0.0000 -0.0168 0.1991 0.270 + 47 -9.7556 3.0486 2.8543 2.4858 0.0164 1.0087 0.8218 -0.0025 0.0000 -0.0165 0.1991 0.270 + 48 -10.6786 2.8657 2.6239 2.3396 0.0173 1.0100 0.8229 -0.0030 0.0000 -0.0162 0.1990 0.270 + 49 -11.5760 2.6879 2.3787 2.1960 0.0191 1.0108 0.8236 -0.0036 0.0000 -0.0158 0.1988 0.269 + 50 -12.4328 2.5181 2.1010 2.0545 0.0217 1.0095 0.8225 -0.0041 0.0000 -0.0152 0.1980 0.269 + 51 -13.2400 2.3582 1.8520 1.9140 0.0253 1.0044 0.8183 -0.0045 0.0000 -0.0143 0.1963 0.267 + 52 -13.9941 2.2087 1.6074 1.7721 0.0304 0.9928 0.8089 -0.0047 0.0000 -0.0128 0.1928 0.266 + 53 -14.6868 2.0715 1.3716 1.6247 0.0374 0.9706 0.7908 -0.0045 0.0000 -0.0105 0.1867 0.263 + 54 -15.3105 1.9479 1.1479 1.4662 0.0464 0.9314 0.7589 -0.0040 0.0000 -0.0072 0.1766 0.259 + 55 -15.8583 1.8393 0.9381 1.2884 0.0565 0.8665 0.7060 -0.0023 0.0000 -0.0037 0.1617 0.255 + 56 -16.3244 1.7470 0.7427 1.0847 0.0666 0.7672 0.6251 0.0040 0.0000 -0.0052 0.1451 0.258 + 57 -16.6722 1.4928 0.4131 0.8643 0.0776 1.9578 0.5860 -0.0213 0.0000 -0.0076 0.0758 0.263 + 58 -16.9098 1.1466 0.2292 0.6405 0.0930 1.9003 0.5688 -0.0481 0.0000 0.0150 0.0629 0.224 + 59 -17.0696 0.9138 0.1104 0.3958 0.1055 1.4868 0.4451 -0.0689 0.0000 0.0364 0.0375 0.168 + 60 -17.1499 0.7967 0.0322 0.1341 0.1125 0.5881 0.1760 -0.0517 0.0000 0.0235 0.0103 0.116 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04182 Clsurf = -0.00438 - CYsurf = -0.00662 Cmsurf = -0.20468 - CDsurf = 0.00316 Cnsurf = 0.00366 - CDisurf = 0.00316 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04169 Clsurf = -0.00437 + CYsurf = -0.00660 Cmsurf = -0.20403 + CDsurf = 0.00315 Cnsurf = 0.00365 + CDisurf = 0.00315 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25486 CDsurf = 0.01901 + CLsurf = 0.25403 CDsurf = 0.01897 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.9746 0.1219 0.2844 0.2170 0.1046 0.0000 -0.0115 -0.0592 0.303 - 62 0.0418 4.2566 0.2392 0.8536 0.1223 0.2605 0.1988 0.0264 0.0000 -0.0114 -0.0533 0.307 - 63 0.1156 4.2274 0.3930 0.8449 0.1224 0.2604 0.1987 0.0214 0.0000 -0.0108 -0.0526 0.304 - 64 0.2254 4.1839 0.5386 0.8424 0.1220 0.2625 0.2003 0.0202 0.0000 -0.0097 -0.0521 0.299 - 65 0.3698 4.1268 0.6730 0.8418 0.1208 0.2661 0.2031 0.0198 0.0000 -0.0085 -0.0516 0.292 - 66 0.5474 4.0565 0.7936 0.8415 0.1187 0.2707 0.2066 0.0195 0.0000 -0.0071 -0.0512 0.284 - 67 0.7617 3.9717 0.9441 0.8394 0.1156 0.2759 0.2105 0.0192 0.0000 -0.0058 -0.0510 0.278 - 68 1.0116 3.8728 1.0344 0.8377 0.1111 0.2824 0.2156 0.0191 0.0000 -0.0046 -0.0511 0.271 - 69 1.2891 3.7630 1.1046 0.8340 0.1055 0.2895 0.2209 0.0191 0.0000 -0.0036 -0.0514 0.266 - 70 1.5912 3.6435 1.1542 0.8307 0.0992 0.2979 0.2273 0.0191 0.0000 -0.0028 -0.0521 0.262 - 71 1.9146 3.5155 1.1831 0.8260 0.0928 0.3071 0.2343 0.0192 0.0000 -0.0021 -0.0530 0.259 - 72 2.2558 3.3805 1.1921 0.8201 0.0872 0.3172 0.2421 0.0192 0.0000 -0.0015 -0.0542 0.256 - 73 2.6109 3.2400 1.1821 0.8141 0.0826 0.3285 0.2507 0.0194 0.0000 -0.0010 -0.0557 0.254 - 74 2.9762 3.0955 1.1548 0.8063 0.0793 0.3407 0.2600 0.0196 0.0000 -0.0005 -0.0573 0.252 - 75 3.3476 2.9485 1.1122 0.7973 0.0769 0.3538 0.2700 0.0196 0.0000 0.0000 -0.0590 0.250 - 76 3.7210 2.8008 1.0564 0.7866 0.0752 0.3675 0.2805 0.0197 0.0000 0.0006 -0.0608 0.248 - 77 4.0924 2.6538 0.9900 0.7730 0.0742 0.3813 0.2910 0.0198 0.0000 0.0012 -0.0626 0.246 - 78 4.4577 2.5093 0.9155 0.7566 0.0737 0.3949 0.3014 0.0197 0.0000 0.0020 -0.0642 0.243 - 79 4.8128 2.3687 0.8353 0.7357 0.0739 0.4069 0.3105 0.0195 0.0000 0.0029 -0.0654 0.241 - 80 5.1540 2.2338 0.7518 0.7105 0.0747 0.4168 0.3181 0.0190 0.0000 0.0040 -0.0661 0.237 - 81 5.4774 2.1058 0.6671 0.6803 0.0761 0.4235 0.3232 0.0185 0.0000 0.0055 -0.0659 0.233 - 82 5.7795 1.9862 0.5830 0.6436 0.0782 0.4249 0.3243 0.0174 0.0000 0.0073 -0.0646 0.228 - 83 6.0570 1.8764 0.5012 0.6012 0.0809 0.4203 0.3208 0.0163 0.0000 0.0096 -0.0619 0.220 - 84 6.3069 1.7776 0.4225 0.5513 0.0839 0.4070 0.3106 0.0151 0.0000 0.0122 -0.0575 0.211 - 85 6.5264 1.6907 0.3478 0.4944 0.0871 0.3839 0.2930 0.0132 0.0000 0.0151 -0.0512 0.199 - 86 6.7314 1.6096 0.3326 0.4269 0.0903 0.3483 0.2658 0.0112 0.0000 0.0178 -0.0431 0.183 - 87 6.9144 1.5372 0.2507 0.3445 0.0934 0.2946 0.2248 0.0083 0.0000 0.0194 -0.0328 0.164 - 88 7.0535 1.4822 0.1746 0.2529 0.0959 0.2244 0.1713 0.0051 0.0000 0.0182 -0.0220 0.144 + 61 0.0047 4.2713 0.0803 0.9694 0.1220 0.2829 0.2159 0.1037 0.0000 -0.0115 -0.0589 0.303 + 62 0.0418 4.2566 0.2392 0.8495 0.1224 0.2592 0.1978 0.0263 0.0000 -0.0114 -0.0530 0.307 + 63 0.1156 4.2274 0.3930 0.8407 0.1225 0.2591 0.1977 0.0213 0.0000 -0.0108 -0.0524 0.304 + 64 0.2254 4.1839 0.5386 0.8382 0.1221 0.2612 0.1994 0.0201 0.0000 -0.0097 -0.0518 0.299 + 65 0.3698 4.1268 0.6730 0.8379 0.1209 0.2648 0.2021 0.0197 0.0000 -0.0084 -0.0514 0.292 + 66 0.5474 4.0565 0.7936 0.8369 0.1188 0.2692 0.2055 0.0194 0.0000 -0.0071 -0.0510 0.285 + 67 0.7617 3.9717 0.9441 0.8358 0.1156 0.2747 0.2096 0.0192 0.0000 -0.0058 -0.0508 0.278 + 68 1.0116 3.8728 1.0344 0.8332 0.1112 0.2809 0.2144 0.0190 0.0000 -0.0046 -0.0508 0.272 + 69 1.2891 3.7630 1.1046 0.8306 0.1056 0.2883 0.2200 0.0190 0.0000 -0.0036 -0.0512 0.267 + 70 1.5912 3.6435 1.1542 0.8268 0.0993 0.2965 0.2263 0.0190 0.0000 -0.0028 -0.0519 0.262 + 71 1.9146 3.5155 1.1831 0.8221 0.0929 0.3056 0.2333 0.0191 0.0000 -0.0021 -0.0528 0.259 + 72 2.2558 3.3805 1.1921 0.8166 0.0873 0.3158 0.2410 0.0192 0.0000 -0.0015 -0.0540 0.256 + 73 2.6109 3.2400 1.1821 0.8107 0.0828 0.3272 0.2497 0.0194 0.0000 -0.0010 -0.0555 0.254 + 74 2.9762 3.0955 1.1548 0.8036 0.0794 0.3395 0.2591 0.0196 0.0000 -0.0005 -0.0571 0.252 + 75 3.3476 2.9485 1.1122 0.7949 0.0770 0.3527 0.2692 0.0197 0.0000 0.0000 -0.0588 0.250 + 76 3.7210 2.8008 1.0564 0.7841 0.0753 0.3664 0.2796 0.0198 0.0000 0.0006 -0.0606 0.248 + 77 4.0924 2.6538 0.9900 0.7710 0.0742 0.3803 0.2903 0.0197 0.0000 0.0012 -0.0624 0.246 + 78 4.4577 2.5093 0.9155 0.7548 0.0738 0.3939 0.3006 0.0196 0.0000 0.0020 -0.0640 0.244 + 79 4.8128 2.3687 0.8353 0.7343 0.0739 0.4061 0.3099 0.0194 0.0000 0.0029 -0.0653 0.241 + 80 5.1540 2.2338 0.7518 0.7094 0.0747 0.4161 0.3176 0.0190 0.0000 0.0040 -0.0660 0.237 + 81 5.4774 2.1058 0.6671 0.6791 0.0762 0.4227 0.3226 0.0185 0.0000 0.0055 -0.0658 0.233 + 82 5.7795 1.9862 0.5830 0.6428 0.0783 0.4244 0.3239 0.0174 0.0000 0.0073 -0.0645 0.227 + 83 6.0570 1.8764 0.5012 0.6004 0.0809 0.4197 0.3203 0.0164 0.0000 0.0096 -0.0619 0.220 + 84 6.3069 1.7776 0.4225 0.5509 0.0840 0.4067 0.3104 0.0151 0.0000 0.0122 -0.0574 0.211 + 85 6.5264 1.6907 0.3478 0.4941 0.0871 0.3836 0.2928 0.0132 0.0000 0.0151 -0.0512 0.198 + 86 6.7314 1.6096 0.3326 0.4265 0.0903 0.3480 0.2656 0.0111 0.0000 0.0177 -0.0430 0.183 + 87 6.9144 1.5372 0.2507 0.3442 0.0934 0.2943 0.2246 0.0083 0.0000 0.0193 -0.0327 0.164 + 88 7.0535 1.4822 0.1746 0.2528 0.0959 0.2244 0.1712 0.0052 0.0000 0.0182 -0.0220 0.144 89 7.1471 1.4451 0.1029 0.1546 0.0976 0.1409 0.1075 0.0022 0.0000 0.0134 -0.0122 0.126 - 90 7.1941 1.4265 0.0340 0.0521 0.0985 0.0483 0.0369 -0.0008 0.0000 0.0050 -0.0038 0.116 + 90 7.1941 1.4265 0.0340 0.0520 0.0985 0.0483 0.0368 -0.0008 0.0000 0.0049 -0.0038 0.116 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04182 Clsurf = 0.00438 - CYsurf = 0.00662 Cmsurf = -0.20468 - CDsurf = 0.00316 Cnsurf = -0.00366 - CDisurf = 0.00316 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04169 Clsurf = 0.00437 + CYsurf = 0.00660 Cmsurf = -0.20403 + CDsurf = 0.00315 Cnsurf = -0.00365 + CDisurf = 0.00315 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25486 CDsurf = 0.01901 + CLsurf = 0.25403 CDsurf = 0.01897 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.9746 0.1219 0.2844 0.2170 0.1046 0.0000 -0.0115 0.0592 0.303 - 92 -0.0418 4.2566 0.2392 0.8536 0.1223 0.2605 0.1988 0.0264 0.0000 -0.0114 0.0533 0.307 - 93 -0.1156 4.2274 0.3930 0.8449 0.1224 0.2604 0.1987 0.0214 0.0000 -0.0108 0.0526 0.304 - 94 -0.2254 4.1839 0.5386 0.8424 0.1220 0.2625 0.2003 0.0202 0.0000 -0.0097 0.0521 0.299 - 95 -0.3698 4.1268 0.6730 0.8418 0.1208 0.2661 0.2031 0.0198 0.0000 -0.0085 0.0516 0.292 - 96 -0.5474 4.0565 0.7936 0.8415 0.1187 0.2707 0.2066 0.0195 0.0000 -0.0071 0.0512 0.284 - 97 -0.7617 3.9717 0.9441 0.8393 0.1156 0.2759 0.2105 0.0192 0.0000 -0.0058 0.0510 0.278 - 98 -1.0116 3.8728 1.0344 0.8377 0.1111 0.2824 0.2156 0.0191 0.0000 -0.0046 0.0511 0.271 - 99 -1.2891 3.7630 1.1046 0.8340 0.1055 0.2895 0.2209 0.0191 0.0000 -0.0036 0.0514 0.266 - 100 -1.5912 3.6435 1.1542 0.8307 0.0992 0.2979 0.2273 0.0191 0.0000 -0.0028 0.0521 0.262 - 101 -1.9146 3.5155 1.1831 0.8260 0.0928 0.3071 0.2343 0.0192 0.0000 -0.0021 0.0530 0.259 - 102 -2.2558 3.3805 1.1921 0.8201 0.0872 0.3172 0.2420 0.0192 0.0000 -0.0015 0.0542 0.256 - 103 -2.6109 3.2400 1.1821 0.8141 0.0826 0.3285 0.2507 0.0194 0.0000 -0.0010 0.0557 0.254 - 104 -2.9762 3.0955 1.1548 0.8063 0.0793 0.3407 0.2600 0.0196 0.0000 -0.0005 0.0573 0.252 - 105 -3.3476 2.9485 1.1122 0.7973 0.0769 0.3538 0.2700 0.0196 0.0000 0.0000 0.0590 0.250 - 106 -3.7210 2.8008 1.0564 0.7865 0.0752 0.3675 0.2805 0.0197 0.0000 0.0006 0.0608 0.248 - 107 -4.0924 2.6538 0.9900 0.7730 0.0742 0.3813 0.2910 0.0198 0.0000 0.0012 0.0626 0.246 - 108 -4.4577 2.5093 0.9155 0.7566 0.0737 0.3949 0.3014 0.0197 0.0000 0.0020 0.0642 0.243 - 109 -4.8128 2.3687 0.8353 0.7357 0.0739 0.4068 0.3105 0.0195 0.0000 0.0029 0.0654 0.241 - 110 -5.1540 2.2338 0.7518 0.7105 0.0747 0.4168 0.3181 0.0190 0.0000 0.0040 0.0661 0.237 - 111 -5.4774 2.1058 0.6671 0.6803 0.0761 0.4235 0.3232 0.0185 0.0000 0.0055 0.0659 0.233 - 112 -5.7795 1.9862 0.5830 0.6436 0.0782 0.4249 0.3243 0.0174 0.0000 0.0073 0.0646 0.228 - 113 -6.0570 1.8764 0.5012 0.6012 0.0809 0.4203 0.3208 0.0163 0.0000 0.0096 0.0619 0.220 - 114 -6.3069 1.7776 0.4225 0.5513 0.0839 0.4070 0.3106 0.0151 0.0000 0.0122 0.0575 0.211 - 115 -6.5264 1.6907 0.3478 0.4944 0.0871 0.3839 0.2930 0.0132 0.0000 0.0151 0.0512 0.199 - 116 -6.7314 1.6096 0.3326 0.4269 0.0903 0.3483 0.2658 0.0112 0.0000 0.0178 0.0431 0.183 - 117 -6.9144 1.5372 0.2507 0.3445 0.0934 0.2946 0.2248 0.0083 0.0000 0.0194 0.0328 0.164 - 118 -7.0535 1.4822 0.1746 0.2529 0.0959 0.2244 0.1713 0.0051 0.0000 0.0182 0.0220 0.144 + 91 -0.0047 4.2713 0.0803 0.9694 0.1220 0.2829 0.2159 0.1037 0.0000 -0.0115 0.0589 0.303 + 92 -0.0418 4.2566 0.2392 0.8495 0.1224 0.2592 0.1978 0.0263 0.0000 -0.0114 0.0530 0.307 + 93 -0.1156 4.2274 0.3930 0.8407 0.1225 0.2591 0.1977 0.0213 0.0000 -0.0108 0.0524 0.304 + 94 -0.2254 4.1839 0.5386 0.8382 0.1221 0.2612 0.1994 0.0201 0.0000 -0.0097 0.0518 0.299 + 95 -0.3698 4.1268 0.6730 0.8379 0.1209 0.2648 0.2021 0.0197 0.0000 -0.0084 0.0514 0.292 + 96 -0.5474 4.0565 0.7936 0.8369 0.1188 0.2692 0.2055 0.0194 0.0000 -0.0071 0.0510 0.285 + 97 -0.7617 3.9717 0.9441 0.8358 0.1156 0.2747 0.2096 0.0192 0.0000 -0.0058 0.0508 0.278 + 98 -1.0116 3.8728 1.0344 0.8332 0.1112 0.2809 0.2144 0.0190 0.0000 -0.0046 0.0508 0.272 + 99 -1.2891 3.7630 1.1046 0.8306 0.1056 0.2883 0.2200 0.0190 0.0000 -0.0036 0.0512 0.267 + 100 -1.5912 3.6435 1.1542 0.8268 0.0993 0.2965 0.2263 0.0190 0.0000 -0.0028 0.0519 0.262 + 101 -1.9146 3.5155 1.1831 0.8221 0.0929 0.3056 0.2333 0.0191 0.0000 -0.0021 0.0528 0.259 + 102 -2.2558 3.3805 1.1921 0.8166 0.0873 0.3158 0.2410 0.0192 0.0000 -0.0015 0.0540 0.256 + 103 -2.6109 3.2400 1.1821 0.8107 0.0828 0.3272 0.2497 0.0194 0.0000 -0.0010 0.0555 0.254 + 104 -2.9762 3.0955 1.1548 0.8036 0.0794 0.3395 0.2591 0.0196 0.0000 -0.0005 0.0571 0.252 + 105 -3.3476 2.9485 1.1122 0.7949 0.0770 0.3527 0.2692 0.0197 0.0000 0.0000 0.0588 0.250 + 106 -3.7210 2.8008 1.0564 0.7841 0.0753 0.3664 0.2796 0.0198 0.0000 0.0006 0.0606 0.248 + 107 -4.0924 2.6538 0.9900 0.7710 0.0742 0.3803 0.2903 0.0197 0.0000 0.0012 0.0624 0.246 + 108 -4.4577 2.5093 0.9155 0.7548 0.0738 0.3939 0.3006 0.0196 0.0000 0.0020 0.0640 0.244 + 109 -4.8128 2.3687 0.8353 0.7343 0.0739 0.4061 0.3099 0.0194 0.0000 0.0029 0.0653 0.241 + 110 -5.1540 2.2338 0.7518 0.7094 0.0747 0.4161 0.3176 0.0190 0.0000 0.0040 0.0660 0.237 + 111 -5.4774 2.1058 0.6671 0.6791 0.0762 0.4227 0.3226 0.0185 0.0000 0.0055 0.0658 0.233 + 112 -5.7795 1.9862 0.5830 0.6428 0.0783 0.4244 0.3239 0.0174 0.0000 0.0073 0.0645 0.227 + 113 -6.0570 1.8764 0.5012 0.6004 0.0809 0.4197 0.3203 0.0164 0.0000 0.0096 0.0619 0.220 + 114 -6.3069 1.7776 0.4225 0.5509 0.0840 0.4067 0.3104 0.0151 0.0000 0.0122 0.0574 0.211 + 115 -6.5264 1.6907 0.3478 0.4941 0.0871 0.3836 0.2928 0.0132 0.0000 0.0151 0.0512 0.198 + 116 -6.7314 1.6096 0.3326 0.4265 0.0903 0.3480 0.2656 0.0111 0.0000 0.0177 0.0430 0.183 + 117 -6.9144 1.5372 0.2507 0.3442 0.0934 0.2943 0.2246 0.0083 0.0000 0.0193 0.0327 0.164 + 118 -7.0535 1.4822 0.1746 0.2528 0.0959 0.2244 0.1712 0.0052 0.0000 0.0182 0.0220 0.144 119 -7.1471 1.4451 0.1029 0.1546 0.0976 0.1409 0.1075 0.0022 0.0000 0.0134 0.0122 0.126 - 120 -7.1941 1.4265 0.0340 0.0521 0.0985 0.0483 0.0369 -0.0008 0.0000 0.0050 0.0038 0.116 + 120 -7.1941 1.4265 0.0340 0.0520 0.0985 0.0483 0.0368 -0.0008 0.0000 0.0049 0.0038 0.116 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,67 +198,67 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.371 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.383 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.393 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.399 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.405 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.405 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.395 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.380 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.357 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.317 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.280 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.272 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.260 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.346 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.357 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.367 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.369 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.385 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.380 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.378 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.360 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.347 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.314 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.278 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.262 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.215 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.206 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.198 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.181 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.162 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.142 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.123 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.196 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.177 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.161 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.135 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.122 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.104 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01085 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.06645 + CLsurf = 0.01078 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = 0.06652 CDsurf = -0.00024 Cnsurf = -0.00000 CDisurf = -0.00024 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01093 CDsurf = -0.00024 + CLsurf = 0.01086 CDsurf = -0.00025 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.2467 0.1795 0.1046 0.0097 -0.0031 0.0000 0.0047 0.0003 -0.236 - 152 -1.3090 31.2096 11.6724 0.3492 0.1926 0.0426 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.267 - 153 -0.9350 34.0626 12.7394 0.3828 0.1779 0.0271 0.0113 -0.0002 0.0000 0.0070 0.0014 -0.371 - 154 -0.5610 36.1619 13.5246 0.4013 0.1729 0.0185 0.0111 0.0005 0.0000 0.0076 0.0022 -0.433 - 155 -0.1870 37.5332 14.0374 0.4119 0.1730 0.0126 0.0109 0.0016 0.0000 0.0077 0.0034 -0.462 - 156 0.1870 37.5332 14.0374 0.4119 0.1730 0.0126 0.0109 0.0016 0.0000 0.0077 0.0034 -0.462 - 157 0.5610 36.1619 13.5246 0.4013 0.1729 0.0185 0.0111 0.0005 0.0000 0.0076 0.0022 -0.433 - 158 0.9350 34.0626 12.7394 0.3828 0.1779 0.0271 0.0113 -0.0002 0.0000 0.0070 0.0014 -0.371 - 159 1.3090 31.2096 11.6724 0.3492 0.1926 0.0426 0.0114 -0.0010 0.0000 0.0059 0.0008 -0.267 - 160 1.6830 26.5957 9.9468 0.2467 0.1795 0.1046 0.0097 -0.0031 0.0000 0.0047 0.0003 -0.236 + 151 -1.6830 26.5957 9.9468 0.2449 0.1795 0.1039 0.0097 -0.0031 0.0000 0.0048 0.0003 -0.242 + 152 -1.3090 31.2096 11.6724 0.3469 0.1926 0.0423 0.0113 -0.0010 0.0000 0.0059 0.0008 -0.272 + 153 -0.9350 34.0626 12.7394 0.3803 0.1780 0.0270 0.0113 -0.0002 0.0000 0.0071 0.0014 -0.377 + 154 -0.5610 36.1619 13.5246 0.3988 0.1731 0.0184 0.0110 0.0005 0.0000 0.0076 0.0022 -0.439 + 155 -0.1870 37.5332 14.0374 0.4094 0.1732 0.0125 0.0108 0.0016 0.0000 0.0077 0.0035 -0.468 + 156 0.1870 37.5332 14.0374 0.4094 0.1732 0.0125 0.0108 0.0016 0.0000 0.0077 0.0035 -0.468 + 157 0.5610 36.1619 13.5246 0.3988 0.1731 0.0184 0.0110 0.0005 0.0000 0.0076 0.0022 -0.439 + 158 0.9350 34.0626 12.7394 0.3803 0.1780 0.0270 0.0113 -0.0002 0.0000 0.0071 0.0014 -0.377 + 159 1.3090 31.2096 11.6724 0.3469 0.1926 0.0423 0.0113 -0.0010 0.0000 0.0059 0.0008 -0.272 + 160 1.6830 26.5957 9.9468 0.2449 0.1795 0.1039 0.0097 -0.0031 0.0000 0.0048 0.0003 -0.242 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 + CLsurf = 0.00000 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = 0.00000 Cnsurf = -0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0001 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.675 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.242 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.015 - 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.385 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.493 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.570 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.639 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.436 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.123 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.127 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.435 + 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.549 + 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.603 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.656 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.730 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_03_06.txt b/regression/scripts/AVL/avl_files/strip_forces_case_03_06.txt index c5bfd87e53..bee1e5483a 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_03_06.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_03_06.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.50188 Clsurf = -0.09843 - CYsurf = -0.02311 Cmsurf = -0.45265 - CDsurf = 0.02183 Cnsurf = -0.01538 - CDisurf = 0.02183 CDvsurf = 0.00000 + CLsurf = 0.50262 Clsurf = -0.09849 + CYsurf = -0.02269 Cmsurf = -0.45294 + CDsurf = 0.02115 Cnsurf = -0.01543 + CDisurf = 0.02115 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.98042 CDsurf = 0.04260 + CLsurf = 0.98181 CDsurf = 0.04128 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 6.3907 0.2273 0.8570 0.6651 0.9719 0.0000 -0.0411 -0.2037 0.312 - 2 0.1025 7.6885 1.0492 5.7245 0.2271 0.9309 0.7225 0.1896 0.0000 -0.0415 -0.1878 0.307 - 3 0.2837 7.5620 1.7073 5.6696 0.2259 0.9487 0.7363 0.1412 0.0000 -0.0385 -0.1864 0.302 - 4 0.5530 7.3741 2.3052 5.6432 0.2228 0.9725 0.7548 0.1260 0.0000 -0.0339 -0.1859 0.295 - 5 0.9075 7.1267 2.8223 5.6021 0.2157 1.0029 0.7783 0.1123 0.0000 -0.0289 -0.1862 0.287 - 6 1.3432 6.8226 3.2414 5.5386 0.1986 1.0388 0.8062 0.1024 0.0000 -0.0242 -0.1877 0.280 - 7 1.8554 6.4651 3.5491 5.4466 0.1616 1.0810 0.8390 0.0933 0.0000 -0.0204 -0.1910 0.274 - 8 2.4386 6.0582 3.7368 5.2982 0.1253 1.1278 0.8753 0.0722 0.0000 -0.0182 -0.1959 0.271 - 9 3.0862 5.6062 3.8005 5.1208 0.1097 1.1809 0.9165 0.0621 0.0000 -0.0172 -0.2030 0.269 - 10 3.7613 5.1351 3.4440 4.9045 0.0972 1.2397 0.9621 0.0439 0.0000 -0.0179 -0.2123 0.269 - 11 4.4532 4.6522 3.3149 4.6734 0.0814 1.3075 1.0147 0.0303 0.0000 -0.0199 -0.2241 0.270 - 12 5.1831 4.1429 3.0930 4.4028 0.0561 1.3885 1.0776 0.0089 0.0000 -0.0216 -0.2375 0.270 - 13 6.0123 3.7903 3.4706 4.1238 0.0385 1.3580 1.1050 -0.0011 0.0000 -0.0164 -0.2625 0.265 - 14 6.9353 3.6075 3.3775 3.9044 0.0347 1.3503 1.0988 0.0017 0.0000 -0.0165 -0.2613 0.265 - 15 7.8737 3.4215 3.2389 3.7030 0.0288 1.3504 1.0988 0.0013 0.0000 -0.0163 -0.2611 0.265 - 16 8.8172 3.2345 3.0619 3.5104 0.0250 1.3544 1.1021 0.0001 0.0000 -0.0160 -0.2615 0.265 - 17 9.7556 3.0486 2.8543 3.3190 0.0241 1.3590 1.1058 -0.0013 0.0000 -0.0157 -0.2620 0.264 - 18 10.6786 2.8657 2.6240 3.1305 0.0251 1.3639 1.1098 -0.0027 0.0000 -0.0153 -0.2625 0.264 - 19 11.5760 2.6879 2.3787 2.9434 0.0274 1.3675 1.1127 -0.0041 0.0000 -0.0147 -0.2626 0.263 - 20 12.4328 2.5181 2.1010 2.7575 0.0309 1.3678 1.1130 -0.0054 0.0000 -0.0139 -0.2619 0.263 - 21 13.2400 2.3582 1.8520 2.5719 0.0358 1.3624 1.1086 -0.0063 0.0000 -0.0127 -0.2598 0.261 - 22 13.9941 2.2087 1.6074 2.3831 0.0427 1.3480 1.0968 -0.0068 0.0000 -0.0107 -0.2554 0.260 - 23 14.6868 2.0715 1.3716 2.1862 0.0521 1.3186 1.0729 -0.0068 0.0000 -0.0076 -0.2474 0.257 - 24 15.3105 1.9479 1.1479 1.9738 0.0642 1.2659 1.0301 -0.0061 0.0000 -0.0031 -0.2338 0.253 - 25 15.8583 1.8393 0.9381 1.7344 0.0778 1.1775 0.9581 -0.0031 0.0000 0.0013 -0.2138 0.249 - 26 16.3244 1.7470 0.7427 1.4603 0.0915 1.0413 0.8473 0.0085 0.0000 -0.0014 -0.1918 0.252 - 27 16.6722 1.4928 0.4131 1.1625 0.1061 2.6110 0.7980 -0.0385 0.0000 -0.0052 -0.1023 0.256 - 28 16.9098 1.1466 0.2292 0.8605 0.1258 2.5459 0.7781 -0.0879 0.0000 0.0253 -0.0849 0.218 - 29 17.0696 0.9138 0.1104 0.5311 0.1416 2.0064 0.6132 -0.1264 0.0000 0.0534 -0.0505 0.163 - 30 17.1499 0.7967 0.0322 0.1797 0.1497 0.8068 0.2466 -0.0964 0.0000 0.0337 -0.0138 0.113 + 1 0.0114 7.7520 0.3539 6.4088 0.2273 0.8599 0.6674 0.9728 0.0000 -0.0427 -0.2055 0.314 + 2 0.1025 7.6885 1.0491 5.7399 0.2272 0.9335 0.7245 0.1896 0.0000 -0.0428 -0.1892 0.309 + 3 0.2837 7.5620 1.7073 5.6847 0.2262 0.9515 0.7385 0.1404 0.0000 -0.0398 -0.1879 0.304 + 4 0.5530 7.3741 2.3052 5.6552 0.2233 0.9756 0.7572 0.1220 0.0000 -0.0352 -0.1873 0.297 + 5 0.9075 7.1267 2.8223 5.6165 0.2163 1.0055 0.7804 0.1123 0.0000 -0.0302 -0.1876 0.289 + 6 1.3432 6.8226 3.2414 5.5491 0.1992 1.0419 0.8086 0.0975 0.0000 -0.0256 -0.1891 0.282 + 7 1.8554 6.4651 3.5491 5.4485 0.1622 1.0849 0.8420 0.0779 0.0000 -0.0219 -0.1922 0.276 + 8 2.4386 6.0582 3.7368 5.3136 0.1259 1.1309 0.8777 0.0728 0.0000 -0.0192 -0.1972 0.272 + 9 3.0862 5.6062 3.8005 5.1336 0.1105 1.1842 0.9191 0.0609 0.0000 -0.0180 -0.2042 0.270 + 10 3.7613 5.1351 3.4440 4.9056 0.0978 1.2389 0.9615 0.0483 0.0000 -0.0190 -0.2132 0.270 + 11 4.4532 4.6522 3.3149 4.7011 0.0813 1.3158 1.0212 0.0279 0.0000 -0.0183 -0.2240 0.268 + 12 5.1831 4.1429 3.0930 4.4062 0.0555 1.3902 1.0789 0.0063 0.0000 -0.0204 -0.2368 0.269 + 13 6.0123 3.7903 3.4706 4.1269 0.0380 1.3591 1.1058 -0.0011 0.0000 -0.0150 -0.2614 0.264 + 14 6.9353 3.6075 3.3775 3.9056 0.0345 1.3507 1.0991 0.0017 0.0000 -0.0150 -0.2600 0.264 + 15 7.8737 3.4215 3.2389 3.7042 0.0287 1.3508 1.0991 0.0013 0.0000 -0.0148 -0.2598 0.263 + 16 8.8172 3.2345 3.0619 3.5118 0.0249 1.3549 1.1025 0.0001 0.0000 -0.0144 -0.2602 0.263 + 17 9.7556 3.0486 2.8543 3.3204 0.0240 1.3595 1.1062 -0.0014 0.0000 -0.0141 -0.2607 0.263 + 18 10.6786 2.8657 2.6239 3.1315 0.0251 1.3643 1.1101 -0.0027 0.0000 -0.0137 -0.2612 0.262 + 19 11.5760 2.6879 2.3787 2.9442 0.0274 1.3679 1.1130 -0.0041 0.0000 -0.0132 -0.2613 0.262 + 20 12.4328 2.5181 2.1010 2.7583 0.0308 1.3682 1.1133 -0.0054 0.0000 -0.0123 -0.2606 0.261 + 21 13.2400 2.3582 1.8520 2.5725 0.0357 1.3628 1.1089 -0.0063 0.0000 -0.0111 -0.2585 0.260 + 22 13.9941 2.2087 1.6074 2.3837 0.0426 1.3483 1.0971 -0.0069 0.0000 -0.0091 -0.2541 0.258 + 23 14.6868 2.0715 1.3716 2.1867 0.0521 1.3189 1.0732 -0.0069 0.0000 -0.0060 -0.2460 0.256 + 24 15.3105 1.9479 1.1479 1.9739 0.0642 1.2660 1.0301 -0.0061 0.0000 -0.0016 -0.2324 0.252 + 25 15.8583 1.8393 0.9381 1.7345 0.0777 1.1776 0.9582 -0.0032 0.0000 0.0029 -0.2124 0.247 + 26 16.3244 1.7470 0.7427 1.4599 0.0913 1.0411 0.8471 0.0084 0.0000 0.0002 -0.1904 0.250 + 27 16.6722 1.4928 0.4131 1.1620 0.1058 2.6101 0.7977 -0.0389 0.0000 -0.0039 -0.1017 0.255 + 28 16.9098 1.1466 0.2292 0.8603 0.1258 2.5457 0.7780 -0.0882 0.0000 0.0263 -0.0844 0.216 + 29 17.0696 0.9138 0.1104 0.5311 0.1417 2.0067 0.6133 -0.1268 0.0000 0.0540 -0.0503 0.162 + 30 17.1499 0.7967 0.0322 0.1798 0.1504 0.8074 0.2468 -0.0970 0.0000 0.0338 -0.0137 0.113 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.50188 Clsurf = 0.09843 - CYsurf = 0.02311 Cmsurf = -0.45265 - CDsurf = 0.02183 Cnsurf = 0.01538 - CDisurf = 0.02183 CDvsurf = 0.00000 + CLsurf = 0.50262 Clsurf = 0.09849 + CYsurf = 0.02269 Cmsurf = -0.45294 + CDsurf = 0.02115 Cnsurf = 0.01543 + CDisurf = 0.02115 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.98042 CDsurf = 0.04260 + CLsurf = 0.98181 CDsurf = 0.04128 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 6.3907 0.2275 0.8570 0.6651 0.9720 0.0000 -0.0411 0.2037 0.312 - 32 -0.1025 7.6885 1.0492 5.7245 0.2271 0.9309 0.7225 0.1896 0.0000 -0.0415 0.1878 0.307 - 33 -0.2837 7.5620 1.7073 5.6696 0.2259 0.9487 0.7363 0.1412 0.0000 -0.0385 0.1864 0.302 - 34 -0.5530 7.3741 2.3052 5.6431 0.2228 0.9725 0.7548 0.1260 0.0000 -0.0339 0.1859 0.295 - 35 -0.9075 7.1267 2.8223 5.6021 0.2157 1.0029 0.7783 0.1123 0.0000 -0.0289 0.1862 0.287 - 36 -1.3432 6.8226 3.2414 5.5385 0.1986 1.0388 0.8062 0.1024 0.0000 -0.0242 0.1877 0.280 - 37 -1.8554 6.4651 3.5491 5.4465 0.1616 1.0810 0.8389 0.0933 0.0000 -0.0204 0.1910 0.274 - 38 -2.4386 6.0582 3.7368 5.2982 0.1253 1.1278 0.8753 0.0722 0.0000 -0.0182 0.1959 0.271 - 39 -3.0862 5.6062 3.8005 5.1208 0.1097 1.1809 0.9165 0.0621 0.0000 -0.0172 0.2030 0.269 - 40 -3.7613 5.1351 3.4440 4.9045 0.0972 1.2397 0.9621 0.0439 0.0000 -0.0179 0.2123 0.269 - 41 -4.4532 4.6522 3.3149 4.6734 0.0814 1.3075 1.0147 0.0303 0.0000 -0.0199 0.2241 0.270 - 42 -5.1831 4.1429 3.0930 4.4028 0.0561 1.3885 1.0776 0.0089 0.0000 -0.0216 0.2375 0.270 - 43 -6.0123 3.7903 3.4706 4.1237 0.0385 1.3580 1.1050 -0.0011 0.0000 -0.0164 0.2625 0.265 - 44 -6.9353 3.6075 3.3775 3.9044 0.0347 1.3503 1.0988 0.0017 0.0000 -0.0165 0.2613 0.265 - 45 -7.8737 3.4215 3.2389 3.7029 0.0288 1.3504 1.0988 0.0013 0.0000 -0.0163 0.2611 0.265 - 46 -8.8172 3.2345 3.0619 3.5104 0.0250 1.3544 1.1021 0.0001 0.0000 -0.0160 0.2615 0.265 - 47 -9.7556 3.0486 2.8543 3.3190 0.0241 1.3590 1.1058 -0.0013 0.0000 -0.0157 0.2620 0.264 - 48 -10.6786 2.8657 2.6240 3.1305 0.0251 1.3639 1.1098 -0.0027 0.0000 -0.0153 0.2625 0.264 - 49 -11.5760 2.6879 2.3787 2.9433 0.0274 1.3675 1.1127 -0.0041 0.0000 -0.0147 0.2626 0.263 - 50 -12.4328 2.5181 2.1010 2.7575 0.0309 1.3678 1.1130 -0.0054 0.0000 -0.0139 0.2619 0.263 - 51 -13.2400 2.3582 1.8520 2.5718 0.0358 1.3624 1.1086 -0.0063 0.0000 -0.0127 0.2598 0.261 - 52 -13.9941 2.2087 1.6074 2.3831 0.0427 1.3480 1.0968 -0.0068 0.0000 -0.0107 0.2554 0.260 - 53 -14.6868 2.0715 1.3716 2.1862 0.0521 1.3186 1.0729 -0.0068 0.0000 -0.0076 0.2473 0.257 - 54 -15.3105 1.9479 1.1479 1.9738 0.0642 1.2659 1.0301 -0.0061 0.0000 -0.0031 0.2338 0.253 - 55 -15.8583 1.8393 0.9381 1.7344 0.0778 1.1775 0.9581 -0.0031 0.0000 0.0013 0.2138 0.249 - 56 -16.3244 1.7470 0.7427 1.4603 0.0915 1.0413 0.8473 0.0085 0.0000 -0.0014 0.1918 0.252 - 57 -16.6722 1.4928 0.4131 1.1625 0.1061 2.6110 0.7980 -0.0385 0.0000 -0.0052 0.1023 0.256 - 58 -16.9098 1.1466 0.2292 0.8604 0.1258 2.5459 0.7781 -0.0879 0.0000 0.0253 0.0849 0.218 - 59 -17.0696 0.9138 0.1104 0.5311 0.1416 2.0064 0.6132 -0.1264 0.0000 0.0534 0.0505 0.163 - 60 -17.1499 0.7967 0.0322 0.1797 0.1497 0.8068 0.2466 -0.0964 0.0000 0.0337 0.0138 0.113 + 31 -0.0114 7.7520 0.3539 6.4088 0.2274 0.8599 0.6674 0.9728 0.0000 -0.0427 0.2055 0.314 + 32 -0.1025 7.6885 1.0491 5.7399 0.2272 0.9335 0.7245 0.1896 0.0000 -0.0428 0.1892 0.309 + 33 -0.2837 7.5620 1.7073 5.6847 0.2262 0.9515 0.7385 0.1404 0.0000 -0.0398 0.1879 0.304 + 34 -0.5530 7.3741 2.3052 5.6552 0.2233 0.9756 0.7572 0.1219 0.0000 -0.0352 0.1873 0.297 + 35 -0.9075 7.1267 2.8223 5.6165 0.2163 1.0055 0.7804 0.1123 0.0000 -0.0302 0.1876 0.289 + 36 -1.3432 6.8226 3.2414 5.5491 0.1992 1.0419 0.8086 0.0975 0.0000 -0.0256 0.1891 0.282 + 37 -1.8554 6.4651 3.5491 5.4485 0.1622 1.0849 0.8420 0.0779 0.0000 -0.0219 0.1922 0.276 + 38 -2.4386 6.0582 3.7368 5.3136 0.1259 1.1309 0.8777 0.0728 0.0000 -0.0192 0.1972 0.272 + 39 -3.0862 5.6062 3.8005 5.1336 0.1105 1.1842 0.9191 0.0609 0.0000 -0.0180 0.2042 0.270 + 40 -3.7613 5.1351 3.4440 4.9056 0.0978 1.2389 0.9615 0.0483 0.0000 -0.0190 0.2132 0.270 + 41 -4.4532 4.6522 3.3149 4.7011 0.0813 1.3158 1.0212 0.0279 0.0000 -0.0183 0.2240 0.268 + 42 -5.1831 4.1429 3.0930 4.4062 0.0555 1.3902 1.0789 0.0063 0.0000 -0.0204 0.2368 0.269 + 43 -6.0123 3.7903 3.4706 4.1269 0.0380 1.3591 1.1058 -0.0011 0.0000 -0.0150 0.2614 0.264 + 44 -6.9353 3.6075 3.3775 3.9056 0.0345 1.3507 1.0991 0.0017 0.0000 -0.0150 0.2600 0.264 + 45 -7.8737 3.4215 3.2389 3.7042 0.0287 1.3508 1.0991 0.0013 0.0000 -0.0148 0.2598 0.263 + 46 -8.8172 3.2345 3.0619 3.5118 0.0249 1.3549 1.1025 0.0001 0.0000 -0.0144 0.2602 0.263 + 47 -9.7556 3.0486 2.8543 3.3204 0.0240 1.3595 1.1062 -0.0014 0.0000 -0.0141 0.2607 0.263 + 48 -10.6786 2.8657 2.6239 3.1315 0.0251 1.3643 1.1101 -0.0027 0.0000 -0.0137 0.2612 0.262 + 49 -11.5760 2.6879 2.3787 2.9442 0.0274 1.3679 1.1130 -0.0041 0.0000 -0.0132 0.2613 0.262 + 50 -12.4328 2.5181 2.1010 2.7583 0.0308 1.3682 1.1133 -0.0054 0.0000 -0.0123 0.2606 0.261 + 51 -13.2400 2.3582 1.8520 2.5725 0.0357 1.3628 1.1089 -0.0063 0.0000 -0.0111 0.2585 0.260 + 52 -13.9941 2.2087 1.6074 2.3837 0.0426 1.3483 1.0971 -0.0069 0.0000 -0.0091 0.2541 0.258 + 53 -14.6868 2.0715 1.3716 2.1867 0.0521 1.3189 1.0732 -0.0069 0.0000 -0.0060 0.2460 0.256 + 54 -15.3105 1.9479 1.1479 1.9739 0.0642 1.2660 1.0301 -0.0061 0.0000 -0.0016 0.2324 0.252 + 55 -15.8583 1.8393 0.9381 1.7345 0.0777 1.1776 0.9582 -0.0032 0.0000 0.0029 0.2124 0.247 + 56 -16.3244 1.7470 0.7427 1.4599 0.0913 1.0411 0.8471 0.0084 0.0000 0.0002 0.1904 0.250 + 57 -16.6722 1.4928 0.4131 1.1620 0.1058 2.6101 0.7977 -0.0389 0.0000 -0.0039 0.1017 0.255 + 58 -16.9098 1.1466 0.2292 0.8603 0.1258 2.5457 0.7780 -0.0882 0.0000 0.0263 0.0844 0.216 + 59 -17.0696 0.9138 0.1104 0.5311 0.1417 2.0067 0.6133 -0.1268 0.0000 0.0540 0.0503 0.162 + 60 -17.1499 0.7967 0.0322 0.1798 0.1504 0.8074 0.2468 -0.0970 0.0000 0.0338 0.0137 0.113 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06464 Clsurf = -0.00665 - CYsurf = -0.01020 Cmsurf = -0.31718 - CDsurf = 0.00662 Cnsurf = 0.00539 - CDisurf = 0.00662 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06450 Clsurf = -0.00664 + CYsurf = -0.01018 Cmsurf = -0.31651 + CDsurf = 0.00660 Cnsurf = 0.00538 + CDisurf = 0.00660 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39385 CDsurf = 0.03983 + CLsurf = 0.39299 CDsurf = 0.03975 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.6761 0.1690 0.4633 0.3521 0.2617 0.0000 -0.0170 -0.1001 0.298 - 62 0.0418 4.2566 0.2392 1.3672 0.1697 0.4149 0.3154 0.0606 0.0000 -0.0170 -0.0851 0.304 - 63 0.1156 4.2274 0.3930 1.3448 0.1700 0.4138 0.3146 0.0475 0.0000 -0.0160 -0.0837 0.301 - 64 0.2254 4.1839 0.5386 1.3378 0.1694 0.4167 0.3168 0.0445 0.0000 -0.0143 -0.0827 0.295 - 65 0.3698 4.1268 0.6730 1.3359 0.1679 0.4223 0.3210 0.0434 0.0000 -0.0123 -0.0819 0.288 - 66 0.5474 4.0565 0.7936 1.3348 0.1651 0.4297 0.3266 0.0423 0.0000 -0.0100 -0.0812 0.281 - 67 0.7617 3.9717 0.9441 1.3293 0.1606 0.4374 0.3325 0.0415 0.0000 -0.0080 -0.0808 0.274 - 68 1.0116 3.8728 1.0344 1.3255 0.1542 0.4477 0.3403 0.0409 0.0000 -0.0061 -0.0809 0.268 - 69 1.2891 3.7630 1.1046 1.3169 0.1461 0.4580 0.3481 0.0406 0.0000 -0.0046 -0.0813 0.263 - 70 1.5912 3.6435 1.1542 1.3099 0.1369 0.4708 0.3579 0.0404 0.0000 -0.0031 -0.0822 0.259 - 71 1.9146 3.5155 1.1831 1.2993 0.1276 0.4843 0.3681 0.0404 0.0000 -0.0020 -0.0835 0.256 - 72 2.2558 3.3805 1.1921 1.2859 0.1195 0.4988 0.3791 0.0402 0.0000 -0.0011 -0.0852 0.253 - 73 2.6109 3.2400 1.1821 1.2721 0.1131 0.5150 0.3915 0.0404 0.0000 -0.0003 -0.0872 0.251 - 74 2.9762 3.0955 1.1548 1.2544 0.1085 0.5319 0.4043 0.0406 0.0000 0.0005 -0.0894 0.249 - 75 3.3476 2.9485 1.1122 1.2347 0.1053 0.5500 0.4180 0.0403 0.0000 0.0012 -0.0917 0.247 - 76 3.7210 2.8008 1.0564 1.2121 0.1033 0.5687 0.4323 0.0404 0.0000 0.0020 -0.0941 0.245 - 77 4.0924 2.6538 0.9900 1.1852 0.1021 0.5872 0.4463 0.0403 0.0000 0.0029 -0.0964 0.243 - 78 4.4577 2.5093 0.9155 1.1545 0.1018 0.6053 0.4601 0.0400 0.0000 0.0041 -0.0985 0.241 - 79 4.8128 2.3687 0.8353 1.1168 0.1023 0.6206 0.4717 0.0393 0.0000 0.0054 -0.0999 0.239 - 80 5.1540 2.2338 0.7518 1.0737 0.1037 0.6331 0.4812 0.0383 0.0000 0.0070 -0.1006 0.235 - 81 5.4774 2.1058 0.6671 1.0239 0.1061 0.6409 0.4871 0.0371 0.0000 0.0091 -0.1001 0.231 - 82 5.7795 1.9862 0.5830 0.9649 0.1093 0.6408 0.4871 0.0348 0.0000 0.0117 -0.0978 0.226 - 83 6.0570 1.8764 0.5012 0.8987 0.1134 0.6322 0.4805 0.0325 0.0000 0.0151 -0.0935 0.219 - 84 6.3069 1.7776 0.4225 0.8217 0.1179 0.6105 0.4640 0.0299 0.0000 0.0189 -0.0866 0.209 - 85 6.5264 1.6907 0.3478 0.7352 0.1227 0.5748 0.4369 0.0260 0.0000 0.0230 -0.0772 0.197 - 86 6.7314 1.6096 0.3326 0.6337 0.1275 0.5208 0.3959 0.0220 0.0000 0.0269 -0.0649 0.182 - 87 6.9144 1.5372 0.2507 0.5107 0.1321 0.4401 0.3345 0.0162 0.0000 0.0291 -0.0494 0.163 - 88 7.0535 1.4822 0.1746 0.3744 0.1358 0.3352 0.2547 0.0098 0.0000 0.0273 -0.0333 0.143 - 89 7.1471 1.4451 0.1029 0.2288 0.1384 0.2106 0.1600 0.0040 0.0000 0.0200 -0.0185 0.125 - 90 7.1941 1.4265 0.0340 0.0770 0.1398 0.0726 0.0552 -0.0020 0.0000 0.0074 -0.0058 0.116 + 61 0.0047 4.2713 0.0803 1.6703 0.1691 0.4617 0.3510 0.2603 0.0000 -0.0169 -0.0998 0.298 + 62 0.0418 4.2566 0.2392 1.3631 0.1698 0.4137 0.3144 0.0605 0.0000 -0.0170 -0.0849 0.304 + 63 0.1156 4.2274 0.3930 1.3402 0.1701 0.4124 0.3135 0.0475 0.0000 -0.0160 -0.0834 0.301 + 64 0.2254 4.1839 0.5386 1.3335 0.1695 0.4154 0.3158 0.0442 0.0000 -0.0143 -0.0824 0.295 + 65 0.3698 4.1268 0.6730 1.3320 0.1680 0.4211 0.3201 0.0431 0.0000 -0.0123 -0.0816 0.288 + 66 0.5474 4.0565 0.7936 1.3293 0.1651 0.4279 0.3252 0.0422 0.0000 -0.0101 -0.0809 0.281 + 67 0.7617 3.9717 0.9441 1.3263 0.1607 0.4364 0.3317 0.0416 0.0000 -0.0080 -0.0806 0.274 + 68 1.0116 3.8728 1.0344 1.3201 0.1543 0.4459 0.3389 0.0406 0.0000 -0.0061 -0.0806 0.268 + 69 1.2891 3.7630 1.1046 1.3142 0.1462 0.4571 0.3474 0.0404 0.0000 -0.0045 -0.0811 0.263 + 70 1.5912 3.6435 1.1542 1.3058 0.1370 0.4694 0.3568 0.0402 0.0000 -0.0032 -0.0820 0.259 + 71 1.9146 3.5155 1.1831 1.2950 0.1277 0.4827 0.3669 0.0401 0.0000 -0.0021 -0.0833 0.256 + 72 2.2558 3.3805 1.1921 1.2822 0.1196 0.4973 0.3780 0.0402 0.0000 -0.0011 -0.0849 0.253 + 73 2.6109 3.2400 1.1821 1.2683 0.1132 0.5135 0.3903 0.0405 0.0000 -0.0003 -0.0870 0.251 + 74 2.9762 3.0955 1.1548 1.2521 0.1086 0.5309 0.4035 0.0406 0.0000 0.0004 -0.0892 0.249 + 75 3.3476 2.9485 1.1122 1.2325 0.1055 0.5489 0.4172 0.0405 0.0000 0.0012 -0.0916 0.247 + 76 3.7210 2.8008 1.0564 1.2094 0.1034 0.5674 0.4313 0.0405 0.0000 0.0020 -0.0939 0.245 + 77 4.0924 2.6538 0.9900 1.1832 0.1022 0.5862 0.4456 0.0401 0.0000 0.0029 -0.0963 0.243 + 78 4.4577 2.5093 0.9155 1.1524 0.1019 0.6042 0.4593 0.0397 0.0000 0.0040 -0.0983 0.241 + 79 4.8128 2.3687 0.8353 1.1154 0.1024 0.6199 0.4712 0.0391 0.0000 0.0053 -0.0998 0.239 + 80 5.1540 2.2338 0.7518 1.0727 0.1038 0.6326 0.4808 0.0383 0.0000 0.0070 -0.1005 0.235 + 81 5.4774 2.1058 0.6671 1.0224 0.1061 0.6399 0.4864 0.0371 0.0000 0.0091 -0.0999 0.231 + 82 5.7795 1.9862 0.5830 0.9639 0.1094 0.6402 0.4866 0.0347 0.0000 0.0117 -0.0977 0.226 + 83 6.0570 1.8764 0.5012 0.8977 0.1134 0.6314 0.4799 0.0327 0.0000 0.0150 -0.0934 0.219 + 84 6.3069 1.7776 0.4225 0.8214 0.1180 0.6103 0.4639 0.0299 0.0000 0.0189 -0.0866 0.209 + 85 6.5264 1.6907 0.3478 0.7350 0.1227 0.5747 0.4368 0.0261 0.0000 0.0230 -0.0771 0.197 + 86 6.7314 1.6096 0.3326 0.6334 0.1275 0.5206 0.3957 0.0219 0.0000 0.0268 -0.0648 0.182 + 87 6.9144 1.5372 0.2507 0.5103 0.1322 0.4397 0.3342 0.0161 0.0000 0.0291 -0.0494 0.163 + 88 7.0535 1.4822 0.1746 0.3745 0.1358 0.3352 0.2548 0.0099 0.0000 0.0273 -0.0333 0.143 + 89 7.1471 1.4451 0.1029 0.2289 0.1384 0.2106 0.1601 0.0040 0.0000 0.0200 -0.0185 0.125 + 90 7.1941 1.4265 0.0340 0.0770 0.1398 0.0725 0.0551 -0.0020 0.0000 0.0074 -0.0058 0.116 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06464 Clsurf = 0.00665 - CYsurf = 0.01020 Cmsurf = -0.31718 - CDsurf = 0.00662 Cnsurf = -0.00539 - CDisurf = 0.00662 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06450 Clsurf = 0.00664 + CYsurf = 0.01018 Cmsurf = -0.31651 + CDsurf = 0.00660 Cnsurf = -0.00538 + CDisurf = 0.00660 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39384 CDsurf = 0.03983 + CLsurf = 0.39299 CDsurf = 0.03975 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.6761 0.1690 0.4633 0.3521 0.2617 0.0000 -0.0170 0.1001 0.298 - 92 -0.0418 4.2566 0.2392 1.3672 0.1697 0.4149 0.3154 0.0606 0.0000 -0.0170 0.0851 0.304 - 93 -0.1156 4.2274 0.3930 1.3448 0.1700 0.4138 0.3146 0.0475 0.0000 -0.0160 0.0837 0.301 - 94 -0.2254 4.1839 0.5386 1.3378 0.1694 0.4167 0.3168 0.0445 0.0000 -0.0143 0.0827 0.295 - 95 -0.3698 4.1268 0.6730 1.3359 0.1679 0.4223 0.3210 0.0434 0.0000 -0.0123 0.0819 0.288 - 96 -0.5474 4.0565 0.7936 1.3348 0.1651 0.4297 0.3266 0.0423 0.0000 -0.0100 0.0812 0.281 - 97 -0.7617 3.9717 0.9441 1.3292 0.1606 0.4374 0.3325 0.0415 0.0000 -0.0080 0.0808 0.274 - 98 -1.0116 3.8728 1.0344 1.3255 0.1542 0.4477 0.3403 0.0409 0.0000 -0.0061 0.0809 0.268 - 99 -1.2891 3.7630 1.1046 1.3169 0.1461 0.4580 0.3481 0.0406 0.0000 -0.0046 0.0813 0.263 - 100 -1.5912 3.6435 1.1542 1.3099 0.1369 0.4708 0.3579 0.0404 0.0000 -0.0031 0.0822 0.259 - 101 -1.9146 3.5155 1.1831 1.2993 0.1276 0.4843 0.3681 0.0404 0.0000 -0.0020 0.0835 0.256 - 102 -2.2558 3.3805 1.1921 1.2859 0.1195 0.4988 0.3791 0.0402 0.0000 -0.0011 0.0852 0.253 - 103 -2.6109 3.2400 1.1821 1.2720 0.1131 0.5150 0.3915 0.0404 0.0000 -0.0003 0.0872 0.251 - 104 -2.9762 3.0955 1.1548 1.2544 0.1085 0.5318 0.4043 0.0406 0.0000 0.0005 0.0894 0.249 - 105 -3.3476 2.9485 1.1122 1.2346 0.1053 0.5499 0.4180 0.0403 0.0000 0.0012 0.0917 0.247 - 106 -3.7210 2.8008 1.0564 1.2121 0.1033 0.5687 0.4323 0.0404 0.0000 0.0020 0.0941 0.245 - 107 -4.0924 2.6538 0.9900 1.1852 0.1021 0.5872 0.4463 0.0403 0.0000 0.0029 0.0964 0.243 - 108 -4.4577 2.5093 0.9155 1.1545 0.1018 0.6053 0.4600 0.0400 0.0000 0.0041 0.0985 0.241 - 109 -4.8128 2.3687 0.8353 1.1168 0.1023 0.6206 0.4717 0.0393 0.0000 0.0054 0.0999 0.239 - 110 -5.1540 2.2338 0.7518 1.0737 0.1037 0.6331 0.4812 0.0383 0.0000 0.0070 0.1006 0.235 - 111 -5.4774 2.1058 0.6671 1.0239 0.1061 0.6408 0.4871 0.0371 0.0000 0.0091 0.1001 0.231 - 112 -5.7795 1.9862 0.5830 0.9649 0.1093 0.6408 0.4871 0.0348 0.0000 0.0117 0.0978 0.226 - 113 -6.0570 1.8764 0.5012 0.8987 0.1134 0.6322 0.4805 0.0325 0.0000 0.0151 0.0935 0.219 - 114 -6.3069 1.7776 0.4225 0.8217 0.1179 0.6105 0.4640 0.0299 0.0000 0.0189 0.0866 0.209 - 115 -6.5264 1.6907 0.3478 0.7352 0.1227 0.5748 0.4369 0.0260 0.0000 0.0230 0.0772 0.197 - 116 -6.7314 1.6096 0.3326 0.6337 0.1275 0.5208 0.3958 0.0220 0.0000 0.0269 0.0649 0.182 - 117 -6.9144 1.5372 0.2507 0.5107 0.1321 0.4401 0.3345 0.0162 0.0000 0.0291 0.0494 0.163 - 118 -7.0535 1.4822 0.1746 0.3744 0.1358 0.3352 0.2547 0.0098 0.0000 0.0273 0.0333 0.143 - 119 -7.1471 1.4451 0.1029 0.2288 0.1384 0.2106 0.1600 0.0040 0.0000 0.0200 0.0185 0.125 - 120 -7.1941 1.4265 0.0340 0.0770 0.1398 0.0726 0.0552 -0.0020 0.0000 0.0074 0.0058 0.116 + 91 -0.0047 4.2713 0.0803 1.6703 0.1691 0.4617 0.3510 0.2603 0.0000 -0.0169 0.0998 0.298 + 92 -0.0418 4.2566 0.2392 1.3631 0.1698 0.4137 0.3144 0.0605 0.0000 -0.0170 0.0849 0.304 + 93 -0.1156 4.2274 0.3930 1.3402 0.1701 0.4124 0.3135 0.0475 0.0000 -0.0160 0.0834 0.301 + 94 -0.2254 4.1839 0.5386 1.3335 0.1695 0.4154 0.3158 0.0442 0.0000 -0.0143 0.0824 0.295 + 95 -0.3698 4.1268 0.6730 1.3320 0.1680 0.4211 0.3201 0.0431 0.0000 -0.0123 0.0816 0.288 + 96 -0.5474 4.0565 0.7936 1.3293 0.1651 0.4279 0.3252 0.0422 0.0000 -0.0101 0.0809 0.281 + 97 -0.7617 3.9717 0.9441 1.3263 0.1607 0.4364 0.3317 0.0416 0.0000 -0.0080 0.0806 0.274 + 98 -1.0116 3.8728 1.0344 1.3201 0.1543 0.4459 0.3389 0.0406 0.0000 -0.0061 0.0806 0.268 + 99 -1.2891 3.7630 1.1046 1.3142 0.1462 0.4571 0.3474 0.0404 0.0000 -0.0045 0.0811 0.263 + 100 -1.5912 3.6435 1.1542 1.3058 0.1370 0.4694 0.3568 0.0402 0.0000 -0.0032 0.0820 0.259 + 101 -1.9146 3.5155 1.1831 1.2950 0.1277 0.4827 0.3669 0.0401 0.0000 -0.0021 0.0833 0.256 + 102 -2.2558 3.3805 1.1921 1.2822 0.1196 0.4973 0.3780 0.0402 0.0000 -0.0011 0.0849 0.253 + 103 -2.6109 3.2400 1.1821 1.2683 0.1132 0.5135 0.3903 0.0405 0.0000 -0.0003 0.0870 0.251 + 104 -2.9762 3.0955 1.1548 1.2521 0.1086 0.5309 0.4035 0.0406 0.0000 0.0004 0.0892 0.249 + 105 -3.3476 2.9485 1.1122 1.2325 0.1055 0.5489 0.4172 0.0405 0.0000 0.0012 0.0916 0.247 + 106 -3.7210 2.8008 1.0564 1.2094 0.1034 0.5674 0.4313 0.0405 0.0000 0.0020 0.0939 0.245 + 107 -4.0924 2.6538 0.9900 1.1832 0.1022 0.5862 0.4456 0.0401 0.0000 0.0029 0.0963 0.243 + 108 -4.4577 2.5093 0.9155 1.1524 0.1019 0.6042 0.4593 0.0397 0.0000 0.0040 0.0983 0.241 + 109 -4.8128 2.3687 0.8353 1.1154 0.1024 0.6199 0.4712 0.0391 0.0000 0.0053 0.0998 0.239 + 110 -5.1540 2.2338 0.7518 1.0727 0.1038 0.6326 0.4808 0.0383 0.0000 0.0070 0.1005 0.235 + 111 -5.4774 2.1058 0.6671 1.0224 0.1061 0.6399 0.4864 0.0371 0.0000 0.0091 0.0999 0.231 + 112 -5.7795 1.9862 0.5830 0.9639 0.1094 0.6402 0.4866 0.0347 0.0000 0.0117 0.0977 0.226 + 113 -6.0570 1.8764 0.5012 0.8977 0.1134 0.6314 0.4799 0.0327 0.0000 0.0150 0.0934 0.219 + 114 -6.3069 1.7776 0.4225 0.8214 0.1180 0.6103 0.4639 0.0299 0.0000 0.0189 0.0866 0.209 + 115 -6.5264 1.6907 0.3478 0.7350 0.1227 0.5747 0.4368 0.0261 0.0000 0.0230 0.0771 0.197 + 116 -6.7314 1.6096 0.3326 0.6334 0.1275 0.5206 0.3957 0.0219 0.0000 0.0268 0.0648 0.182 + 117 -6.9144 1.5372 0.2507 0.5103 0.1322 0.4397 0.3342 0.0161 0.0000 0.0291 0.0494 0.163 + 118 -7.0535 1.4822 0.1746 0.3745 0.1358 0.3352 0.2548 0.0099 0.0000 0.0273 0.0333 0.143 + 119 -7.1471 1.4451 0.1029 0.2289 0.1384 0.2106 0.1601 0.0040 0.0000 0.0200 0.0185 0.125 + 120 -7.1941 1.4265 0.0340 0.0770 0.1398 0.0725 0.0551 -0.0020 0.0000 0.0074 0.0058 0.116 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.387 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.399 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.410 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.417 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.422 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.422 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.410 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.393 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.366 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.323 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.283 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.274 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.260 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.252 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.246 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.360 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.371 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.382 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.386 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.401 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.395 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.391 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.372 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.355 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.318 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.281 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.264 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.248 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.208 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.199 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.191 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.174 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.155 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.135 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.116 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.106 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.189 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.170 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.154 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.128 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.096 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01744 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.09526 - CDsurf = -0.00018 Cnsurf = -0.00000 - CDisurf = -0.00018 CDvsurf = 0.00000 + CLsurf = 0.01737 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = 0.09533 + CDsurf = -0.00019 Cnsurf = -0.00000 + CDisurf = -0.00019 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01758 CDsurf = -0.00018 + CLsurf = 0.01751 CDsurf = -0.00019 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.4033 0.2586 0.1527 0.0163 -0.0054 0.0000 0.0063 0.0003 -0.135 - 152 -1.3090 31.2096 11.6724 0.5613 0.2745 0.0665 0.0185 -0.0016 0.0000 0.0080 0.0009 -0.184 - 153 -0.9350 34.0626 12.7394 0.6093 0.2476 0.0426 0.0182 -0.0001 0.0000 0.0099 0.0018 -0.293 - 154 -0.5610 36.1619 13.5246 0.6357 0.2371 0.0291 0.0176 0.0012 0.0000 0.0107 0.0028 -0.358 - 155 -0.1870 37.5332 14.0374 0.6513 0.2356 0.0197 0.0170 0.0033 0.0000 0.0109 0.0046 -0.392 - 156 0.1870 37.5332 14.0374 0.6513 0.2356 0.0197 0.0170 0.0033 0.0000 0.0109 0.0046 -0.392 - 157 0.5610 36.1619 13.5246 0.6357 0.2371 0.0291 0.0176 0.0012 0.0000 0.0107 0.0028 -0.358 - 158 0.9350 34.0626 12.7394 0.6093 0.2476 0.0426 0.0182 -0.0001 0.0000 0.0099 0.0018 -0.293 - 159 1.3090 31.2096 11.6724 0.5613 0.2745 0.0665 0.0185 -0.0016 0.0000 0.0080 0.0009 -0.184 - 160 1.6830 26.5957 9.9468 0.4033 0.2586 0.1527 0.0163 -0.0054 0.0000 0.0063 0.0003 -0.135 + 151 -1.6830 26.5957 9.9468 0.4015 0.2585 0.1521 0.0163 -0.0054 0.0000 0.0063 0.0003 -0.138 + 152 -1.3090 31.2096 11.6724 0.5589 0.2745 0.0662 0.0185 -0.0016 0.0000 0.0081 0.0009 -0.187 + 153 -0.9350 34.0626 12.7394 0.6069 0.2477 0.0424 0.0181 -0.0001 0.0000 0.0099 0.0018 -0.296 + 154 -0.5610 36.1619 13.5246 0.6332 0.2373 0.0289 0.0176 0.0012 0.0000 0.0108 0.0029 -0.362 + 155 -0.1870 37.5332 14.0374 0.6488 0.2359 0.0196 0.0170 0.0033 0.0000 0.0110 0.0046 -0.396 + 156 0.1870 37.5332 14.0374 0.6488 0.2359 0.0196 0.0170 0.0033 0.0000 0.0110 0.0046 -0.396 + 157 0.5610 36.1619 13.5246 0.6332 0.2373 0.0289 0.0176 0.0012 0.0000 0.0108 0.0029 -0.362 + 158 0.9350 34.0626 12.7394 0.6069 0.2477 0.0424 0.0181 -0.0001 0.0000 0.0099 0.0018 -0.296 + 159 1.3090 31.2096 11.6724 0.5589 0.2745 0.0662 0.0185 -0.0016 0.0000 0.0081 0.0009 -0.187 + 160 1.6830 26.5957 9.9468 0.4015 0.2585 0.1521 0.0163 -0.0054 0.0000 0.0063 0.0003 -0.138 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.842 - 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0002 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.320 - 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.352 - 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.502 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.601 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.682 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.777 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.735 + 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.675 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.094 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.427 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.570 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.639 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.700 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.779 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_04_01.txt b/regression/scripts/AVL/avl_files/strip_forces_case_04_01.txt index 13d9504931..85926a0612 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_04_01.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_04_01.txt @@ -7,275 +7,275 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00938 Clsurf = 0.00261 - CYsurf = 0.00011 Cmsurf = 0.00338 + CLsurf = 0.01004 Clsurf = 0.00255 + CYsurf = 0.00008 Cmsurf = 0.00303 CDsurf = 0.00040 Cnsurf = -0.00019 CDisurf = 0.00040 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01825 CDsurf = 0.00078 + CLsurf = 0.01954 CDsurf = 0.00079 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 0.7371 0.0126 0.1233 0.0958 0.0193 0.0000 -0.0046 -0.0231 0.298 - 2 0.1025 7.6885 1.0492 0.7244 0.0117 0.1215 0.0944 0.0047 0.0000 -0.0046 -0.0229 0.299 - 3 0.2837 7.5620 1.7073 0.7197 0.0101 0.1227 0.0954 0.0037 0.0000 -0.0043 -0.0228 0.295 - 4 0.5530 7.3741 2.3052 0.7091 0.0076 0.1239 0.0963 0.0032 0.0000 -0.0039 -0.0227 0.291 - 5 0.9075 7.1267 2.8223 0.6877 0.0051 0.1244 0.0966 0.0026 0.0000 -0.0037 -0.0226 0.288 - 6 1.3432 6.8226 3.2414 0.6517 0.0057 0.1231 0.0957 0.0020 0.0000 -0.0037 -0.0224 0.288 - 7 1.8554 6.4651 3.5491 0.5981 0.0154 0.1192 0.0926 0.0015 0.0000 -0.0040 -0.0221 0.294 - 8 2.4386 6.0582 3.7368 0.5241 0.0229 0.1114 0.0866 0.0007 0.0000 -0.0049 -0.0216 0.306 - 9 3.0862 5.6062 3.8005 0.4311 0.0155 0.0990 0.0769 0.0002 0.0000 -0.0064 -0.0208 0.333 - 10 3.7613 5.1351 3.4440 0.3281 0.0057 0.0823 0.0639 -0.0002 0.0000 -0.0087 -0.0201 0.386 - 11 4.4532 4.6522 3.3149 0.2218 -0.0027 0.0614 0.0477 -0.0003 0.0000 -0.0121 -0.0196 0.505 - 12 5.1831 4.1429 3.0930 0.1123 -0.0130 0.0349 0.0271 -0.0003 0.0000 -0.0169 -0.0193 0.874 - 13 6.0123 3.7903 3.4706 0.0175 -0.0179 0.0056 0.0046 -0.0001 0.0000 -0.0210 -0.0197 - 14 6.9353 3.6075 3.3775 -0.0452 -0.0137 -0.0152 -0.0125 0.0001 0.0000 -0.0218 -0.0166 - 15 7.8737 3.4215 3.2389 -0.0895 -0.0100 -0.0318 -0.0262 0.0002 0.0000 -0.0220 -0.0138 -0.592 - 16 8.8172 3.2345 3.0619 -0.1207 -0.0076 -0.0453 -0.0373 0.0003 0.0000 -0.0221 -0.0114 -0.342 - 17 9.7556 3.0486 2.8543 -0.1419 -0.0065 -0.0565 -0.0466 0.0003 0.0000 -0.0221 -0.0094 -0.225 - 18 10.6786 2.8657 2.6240 -0.1553 -0.0061 -0.0658 -0.0542 0.0003 0.0000 -0.0221 -0.0077 -0.158 - 19 11.5760 2.6879 2.3787 -0.1625 -0.0060 -0.0734 -0.0605 0.0003 0.0000 -0.0221 -0.0063 -0.116 - 20 12.4328 2.5181 2.1010 -0.1647 -0.0062 -0.0794 -0.0654 0.0003 0.0000 -0.0222 -0.0053 -0.089 - 21 13.2400 2.3582 1.8520 -0.1628 -0.0064 -0.0838 -0.0691 0.0002 0.0000 -0.0223 -0.0046 -0.073 - 22 13.9941 2.2087 1.6074 -0.1572 -0.0068 -0.0865 -0.0712 0.0002 0.0000 -0.0225 -0.0043 -0.066 - 23 14.6868 2.0715 1.3716 -0.1482 -0.0074 -0.0869 -0.0716 0.0002 0.0000 -0.0228 -0.0045 -0.068 - 24 15.3105 1.9479 1.1479 -0.1353 -0.0079 -0.0844 -0.0695 0.0001 0.0000 -0.0231 -0.0052 -0.082 - 25 15.8583 1.8393 0.9381 -0.1185 -0.0081 -0.0783 -0.0645 0.0000 0.0000 -0.0230 -0.0062 -0.106 - 26 16.3244 1.7470 0.7427 -0.0981 -0.0081 -0.0682 -0.0562 0.0001 0.0000 -0.0209 -0.0062 -0.123 - 27 16.6722 1.4928 0.4131 -0.0760 -0.0078 -0.1679 -0.0510 -0.0007 0.0000 -0.0162 -0.0018 -0.067 - 28 16.9098 1.1466 0.2292 -0.0537 -0.0064 -0.1544 -0.0469 -0.0010 0.0000 -0.0171 -0.0027 -0.115 - 29 17.0696 0.9138 0.1104 -0.0315 -0.0045 -0.1138 -0.0345 -0.0015 0.0000 -0.0158 -0.0035 -0.207 - 30 17.1499 0.7967 0.0322 -0.0103 -0.0034 -0.0431 -0.0131 -0.0025 0.0000 -0.0075 -0.0020 -0.321 + 1 0.0114 7.7520 0.3539 0.7535 0.0124 0.1260 0.0979 0.0191 0.0000 -0.0060 -0.0246 0.311 + 2 0.1025 7.6885 1.0491 0.7404 0.0117 0.1242 0.0965 0.0047 0.0000 -0.0059 -0.0244 0.311 + 3 0.2837 7.5620 1.7073 0.7359 0.0103 0.1255 0.0975 0.0037 0.0000 -0.0056 -0.0244 0.308 + 4 0.5530 7.3741 2.3052 0.7255 0.0081 0.1268 0.0985 0.0031 0.0000 -0.0053 -0.0243 0.304 + 5 0.9075 7.1267 2.8223 0.7043 0.0057 0.1274 0.0990 0.0027 0.0000 -0.0050 -0.0242 0.301 + 6 1.3432 6.8226 3.2414 0.6681 0.0063 0.1262 0.0981 0.0021 0.0000 -0.0050 -0.0240 0.301 + 7 1.8554 6.4651 3.5491 0.6136 0.0161 0.1223 0.0950 0.0013 0.0000 -0.0053 -0.0236 0.306 + 8 2.4386 6.0582 3.7368 0.5391 0.0236 0.1146 0.0891 0.0008 0.0000 -0.0060 -0.0230 0.317 + 9 3.0862 5.6062 3.8005 0.4451 0.0165 0.1022 0.0795 0.0002 0.0000 -0.0073 -0.0221 0.342 + 10 3.7613 5.1351 3.4440 0.3393 0.0064 0.0851 0.0661 -0.0002 0.0000 -0.0093 -0.0210 0.391 + 11 4.4532 4.6522 3.3149 0.2296 -0.0028 0.0635 0.0494 -0.0003 0.0000 -0.0120 -0.0198 0.493 + 12 5.1831 4.1429 3.0930 0.1164 -0.0137 0.0362 0.0281 -0.0004 0.0000 -0.0159 -0.0187 0.816 + 13 6.0123 3.7903 3.4706 0.0202 -0.0184 0.0065 0.0053 -0.0001 0.0000 -0.0194 -0.0185 + 14 6.9353 3.6075 3.3775 -0.0429 -0.0140 -0.0144 -0.0119 0.0001 0.0000 -0.0201 -0.0153 + 15 7.8737 3.4215 3.2389 -0.0876 -0.0102 -0.0311 -0.0256 0.0002 0.0000 -0.0203 -0.0124 -0.543 + 16 8.8172 3.2345 3.0619 -0.1190 -0.0077 -0.0447 -0.0368 0.0003 0.0000 -0.0203 -0.0100 -0.303 + 17 9.7556 3.0486 2.8543 -0.1405 -0.0066 -0.0560 -0.0461 0.0003 0.0000 -0.0204 -0.0079 -0.191 + 18 10.6786 2.8657 2.6239 -0.1541 -0.0062 -0.0653 -0.0538 0.0003 0.0000 -0.0204 -0.0062 -0.128 + 19 11.5760 2.6879 2.3787 -0.1615 -0.0061 -0.0730 -0.0601 0.0003 0.0000 -0.0204 -0.0049 -0.089 + 20 12.4328 2.5181 2.1010 -0.1639 -0.0062 -0.0790 -0.0651 0.0003 0.0000 -0.0204 -0.0038 -0.064 + 21 13.2400 2.3582 1.8520 -0.1621 -0.0065 -0.0835 -0.0688 0.0002 0.0000 -0.0205 -0.0031 -0.049 + 22 13.9941 2.2087 1.6074 -0.1567 -0.0069 -0.0862 -0.0710 0.0002 0.0000 -0.0207 -0.0028 -0.042 + 23 14.6868 2.0715 1.3716 -0.1478 -0.0074 -0.0867 -0.0714 0.0002 0.0000 -0.0210 -0.0029 -0.044 + 24 15.3105 1.9479 1.1479 -0.1352 -0.0079 -0.0843 -0.0694 0.0001 0.0000 -0.0213 -0.0036 -0.057 + 25 15.8583 1.8393 0.9381 -0.1187 -0.0082 -0.0784 -0.0645 0.0001 0.0000 -0.0212 -0.0046 -0.079 + 26 16.3244 1.7470 0.7427 -0.0986 -0.0084 -0.0686 -0.0565 0.0001 0.0000 -0.0192 -0.0046 -0.090 + 27 16.6722 1.4928 0.4131 -0.0765 -0.0082 -0.1690 -0.0513 -0.0007 0.0000 -0.0148 -0.0011 -0.038 + 28 16.9098 1.1466 0.2292 -0.0539 -0.0065 -0.1550 -0.0470 -0.0010 0.0000 -0.0160 -0.0021 -0.090 + 29 17.0696 0.9138 0.1104 -0.0315 -0.0043 -0.1139 -0.0346 -0.0014 0.0000 -0.0151 -0.0032 -0.187 + 30 17.1499 0.7967 0.0322 -0.0103 -0.0027 -0.0428 -0.0130 -0.0023 0.0000 -0.0073 -0.0019 -0.309 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.00938 Clsurf = -0.00261 - CYsurf = -0.00011 Cmsurf = 0.00338 + CLsurf = 0.01004 Clsurf = -0.00255 + CYsurf = -0.00008 Cmsurf = 0.00303 CDsurf = 0.00040 Cnsurf = 0.00019 CDisurf = 0.00040 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01825 CDsurf = 0.00078 + CLsurf = 0.01954 CDsurf = 0.00079 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 0.7371 0.0125 0.1233 0.0958 0.0193 0.0000 -0.0046 0.0231 0.298 - 32 -0.1025 7.6885 1.0492 0.7243 0.0117 0.1215 0.0944 0.0047 0.0000 -0.0046 0.0229 0.299 - 33 -0.2837 7.5620 1.7073 0.7197 0.0100 0.1227 0.0954 0.0037 0.0000 -0.0043 0.0228 0.295 - 34 -0.5530 7.3741 2.3052 0.7091 0.0076 0.1239 0.0963 0.0032 0.0000 -0.0039 0.0227 0.291 - 35 -0.9075 7.1267 2.8223 0.6877 0.0051 0.1244 0.0966 0.0026 0.0000 -0.0037 0.0226 0.288 - 36 -1.3432 6.8226 3.2414 0.6517 0.0057 0.1231 0.0957 0.0020 0.0000 -0.0037 0.0224 0.288 - 37 -1.8554 6.4651 3.5491 0.5981 0.0154 0.1192 0.0926 0.0015 0.0000 -0.0040 0.0221 0.294 - 38 -2.4386 6.0582 3.7368 0.5241 0.0229 0.1114 0.0866 0.0007 0.0000 -0.0049 0.0216 0.306 - 39 -3.0862 5.6062 3.8005 0.4311 0.0155 0.0990 0.0769 0.0002 0.0000 -0.0064 0.0208 0.333 - 40 -3.7613 5.1351 3.4440 0.3281 0.0057 0.0823 0.0639 -0.0002 0.0000 -0.0087 0.0201 0.386 - 41 -4.4532 4.6522 3.3149 0.2218 -0.0027 0.0614 0.0477 -0.0003 0.0000 -0.0121 0.0196 0.505 - 42 -5.1831 4.1429 3.0930 0.1123 -0.0130 0.0349 0.0271 -0.0003 0.0000 -0.0169 0.0193 0.874 - 43 -6.0123 3.7903 3.4706 0.0175 -0.0179 0.0056 0.0046 -0.0001 0.0000 -0.0210 0.0197 - 44 -6.9353 3.6075 3.3775 -0.0452 -0.0137 -0.0152 -0.0125 0.0001 0.0000 -0.0218 0.0166 - 45 -7.8737 3.4215 3.2389 -0.0895 -0.0100 -0.0318 -0.0262 0.0002 0.0000 -0.0220 0.0138 -0.592 - 46 -8.8172 3.2345 3.0619 -0.1207 -0.0076 -0.0453 -0.0373 0.0003 0.0000 -0.0221 0.0114 -0.342 - 47 -9.7556 3.0486 2.8543 -0.1419 -0.0065 -0.0565 -0.0466 0.0003 0.0000 -0.0221 0.0094 -0.225 - 48 -10.6786 2.8657 2.6240 -0.1553 -0.0061 -0.0658 -0.0542 0.0003 0.0000 -0.0221 0.0077 -0.158 - 49 -11.5760 2.6879 2.3787 -0.1625 -0.0060 -0.0734 -0.0605 0.0003 0.0000 -0.0221 0.0063 -0.116 - 50 -12.4328 2.5181 2.1010 -0.1647 -0.0062 -0.0794 -0.0654 0.0003 0.0000 -0.0222 0.0053 -0.089 - 51 -13.2400 2.3582 1.8520 -0.1628 -0.0064 -0.0838 -0.0691 0.0002 0.0000 -0.0223 0.0046 -0.073 - 52 -13.9941 2.2087 1.6074 -0.1572 -0.0068 -0.0865 -0.0712 0.0002 0.0000 -0.0225 0.0043 -0.066 - 53 -14.6868 2.0715 1.3716 -0.1482 -0.0074 -0.0869 -0.0716 0.0002 0.0000 -0.0228 0.0045 -0.068 - 54 -15.3105 1.9479 1.1479 -0.1353 -0.0079 -0.0844 -0.0695 0.0001 0.0000 -0.0231 0.0052 -0.082 - 55 -15.8583 1.8393 0.9381 -0.1185 -0.0081 -0.0783 -0.0645 0.0000 0.0000 -0.0230 0.0062 -0.106 - 56 -16.3244 1.7470 0.7427 -0.0981 -0.0081 -0.0682 -0.0562 0.0001 0.0000 -0.0209 0.0062 -0.123 - 57 -16.6722 1.4928 0.4131 -0.0760 -0.0078 -0.1679 -0.0510 -0.0007 0.0000 -0.0162 0.0018 -0.067 - 58 -16.9098 1.1466 0.2292 -0.0537 -0.0064 -0.1544 -0.0469 -0.0010 0.0000 -0.0171 0.0027 -0.115 - 59 -17.0696 0.9138 0.1104 -0.0315 -0.0045 -0.1138 -0.0345 -0.0015 0.0000 -0.0158 0.0035 -0.207 - 60 -17.1499 0.7967 0.0322 -0.0103 -0.0034 -0.0431 -0.0131 -0.0025 0.0000 -0.0075 0.0020 -0.321 + 31 -0.0114 7.7520 0.3539 0.7535 0.0124 0.1260 0.0979 0.0191 0.0000 -0.0060 0.0246 0.311 + 32 -0.1025 7.6885 1.0491 0.7404 0.0117 0.1242 0.0965 0.0047 0.0000 -0.0059 0.0244 0.311 + 33 -0.2837 7.5620 1.7073 0.7359 0.0103 0.1255 0.0975 0.0037 0.0000 -0.0056 0.0244 0.308 + 34 -0.5530 7.3741 2.3052 0.7255 0.0081 0.1268 0.0985 0.0031 0.0000 -0.0053 0.0243 0.304 + 35 -0.9075 7.1267 2.8223 0.7043 0.0057 0.1274 0.0990 0.0027 0.0000 -0.0050 0.0242 0.301 + 36 -1.3432 6.8226 3.2414 0.6681 0.0063 0.1262 0.0981 0.0021 0.0000 -0.0050 0.0240 0.301 + 37 -1.8554 6.4651 3.5491 0.6136 0.0161 0.1223 0.0950 0.0013 0.0000 -0.0053 0.0236 0.306 + 38 -2.4386 6.0582 3.7368 0.5391 0.0236 0.1146 0.0891 0.0008 0.0000 -0.0060 0.0230 0.317 + 39 -3.0862 5.6062 3.8005 0.4451 0.0165 0.1022 0.0795 0.0002 0.0000 -0.0073 0.0221 0.342 + 40 -3.7613 5.1351 3.4440 0.3393 0.0064 0.0851 0.0661 -0.0002 0.0000 -0.0093 0.0210 0.391 + 41 -4.4532 4.6522 3.3149 0.2296 -0.0028 0.0635 0.0494 -0.0003 0.0000 -0.0120 0.0198 0.493 + 42 -5.1831 4.1429 3.0930 0.1164 -0.0137 0.0362 0.0281 -0.0004 0.0000 -0.0159 0.0187 0.816 + 43 -6.0123 3.7903 3.4706 0.0202 -0.0184 0.0065 0.0053 -0.0001 0.0000 -0.0194 0.0185 + 44 -6.9353 3.6075 3.3775 -0.0429 -0.0140 -0.0144 -0.0119 0.0001 0.0000 -0.0201 0.0153 + 45 -7.8737 3.4215 3.2389 -0.0876 -0.0102 -0.0311 -0.0256 0.0002 0.0000 -0.0203 0.0124 -0.543 + 46 -8.8172 3.2345 3.0619 -0.1190 -0.0077 -0.0447 -0.0368 0.0003 0.0000 -0.0203 0.0100 -0.303 + 47 -9.7556 3.0486 2.8543 -0.1405 -0.0066 -0.0560 -0.0461 0.0003 0.0000 -0.0204 0.0079 -0.191 + 48 -10.6786 2.8657 2.6239 -0.1541 -0.0062 -0.0653 -0.0538 0.0003 0.0000 -0.0204 0.0062 -0.128 + 49 -11.5760 2.6879 2.3787 -0.1615 -0.0061 -0.0730 -0.0601 0.0003 0.0000 -0.0204 0.0049 -0.089 + 50 -12.4328 2.5181 2.1010 -0.1639 -0.0062 -0.0790 -0.0651 0.0003 0.0000 -0.0204 0.0038 -0.064 + 51 -13.2400 2.3582 1.8520 -0.1621 -0.0065 -0.0835 -0.0688 0.0002 0.0000 -0.0205 0.0031 -0.049 + 52 -13.9941 2.2087 1.6074 -0.1567 -0.0069 -0.0862 -0.0710 0.0002 0.0000 -0.0207 0.0028 -0.042 + 53 -14.6868 2.0715 1.3716 -0.1478 -0.0074 -0.0867 -0.0714 0.0002 0.0000 -0.0210 0.0029 -0.044 + 54 -15.3105 1.9479 1.1479 -0.1352 -0.0079 -0.0843 -0.0694 0.0001 0.0000 -0.0213 0.0036 -0.057 + 55 -15.8583 1.8393 0.9381 -0.1187 -0.0082 -0.0784 -0.0645 0.0001 0.0000 -0.0212 0.0046 -0.079 + 56 -16.3244 1.7470 0.7427 -0.0986 -0.0084 -0.0686 -0.0565 0.0001 0.0000 -0.0192 0.0046 -0.090 + 57 -16.6722 1.4928 0.4131 -0.0765 -0.0082 -0.1690 -0.0513 -0.0007 0.0000 -0.0148 0.0011 -0.038 + 58 -16.9098 1.1466 0.2292 -0.0539 -0.0065 -0.1550 -0.0470 -0.0010 0.0000 -0.0160 0.0021 -0.090 + 59 -17.0696 0.9138 0.1104 -0.0315 -0.0043 -0.1139 -0.0346 -0.0014 0.0000 -0.0151 0.0032 -0.187 + 60 -17.1499 0.7967 0.0322 -0.0103 -0.0027 -0.0428 -0.0130 -0.0023 0.0000 -0.0073 0.0019 -0.309 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02974 Clsurf = 0.00291 - CYsurf = 0.00478 Cmsurf = 0.14271 - CDsurf = 0.00013 Cnsurf = -0.00294 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02990 Clsurf = 0.00292 + CYsurf = 0.00481 Cmsurf = 0.14344 + CDsurf = 0.00013 Cnsurf = -0.00296 CDisurf = 0.00013 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.18132 CDsurf = 0.00079 + CLsurf = -0.18228 CDsurf = 0.00076 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.5971 -0.0211 -0.1765 -0.1377 0.0643 0.0000 0.0091 0.0368 0.316 - 62 0.0418 4.2566 0.2392 -0.6876 -0.0216 -0.2069 -0.1614 0.0076 0.0000 0.0087 0.0411 0.304 - 63 0.1156 4.2274 0.3930 -0.6946 -0.0220 -0.2106 -0.1643 0.0039 0.0000 0.0082 0.0413 0.300 - 64 0.2254 4.1839 0.5386 -0.6965 -0.0223 -0.2135 -0.1665 0.0030 0.0000 0.0074 0.0410 0.294 - 65 0.3698 4.1268 0.6730 -0.6968 -0.0224 -0.2165 -0.1689 0.0025 0.0000 0.0063 0.0406 0.287 - 66 0.5474 4.0565 0.7936 -0.6960 -0.0221 -0.2200 -0.1716 0.0021 0.0000 0.0051 0.0402 0.280 - 67 0.7617 3.9717 0.9441 -0.6943 -0.0215 -0.2242 -0.1749 0.0017 0.0000 0.0040 0.0399 0.273 - 68 1.0116 3.8728 1.0344 -0.6901 -0.0202 -0.2286 -0.1782 0.0013 0.0000 0.0029 0.0397 0.266 - 69 1.2891 3.7630 1.1046 -0.6838 -0.0182 -0.2331 -0.1818 0.0010 0.0000 0.0020 0.0396 0.261 - 70 1.5912 3.6435 1.1542 -0.6742 -0.0159 -0.2374 -0.1851 0.0007 0.0000 0.0012 0.0397 0.257 - 71 1.9146 3.5155 1.1831 -0.6616 -0.0135 -0.2414 -0.1883 0.0004 0.0000 0.0006 0.0398 0.253 - 72 2.2558 3.3805 1.1921 -0.6459 -0.0116 -0.2451 -0.1912 0.0002 0.0000 0.0001 0.0400 0.251 - 73 2.6109 3.2400 1.1821 -0.6265 -0.0106 -0.2481 -0.1935 0.0001 0.0000 -0.0003 0.0402 0.249 - 74 2.9762 3.0955 1.1548 -0.6040 -0.0102 -0.2504 -0.1952 -0.0000 0.0000 -0.0006 0.0403 0.247 - 75 3.3476 2.9485 1.1122 -0.5786 -0.0104 -0.2518 -0.1964 -0.0002 0.0000 -0.0008 0.0403 0.246 - 76 3.7210 2.8008 1.0564 -0.5508 -0.0110 -0.2523 -0.1968 -0.0002 0.0000 -0.0010 0.0402 0.245 - 77 4.0924 2.6538 0.9900 -0.5213 -0.0117 -0.2521 -0.1966 -0.0002 0.0000 -0.0012 0.0400 0.244 - 78 4.4577 2.5093 0.9155 -0.4904 -0.0125 -0.2508 -0.1956 -0.0002 0.0000 -0.0014 0.0396 0.243 - 79 4.8128 2.3687 0.8353 -0.4589 -0.0134 -0.2486 -0.1939 -0.0002 0.0000 -0.0017 0.0390 0.241 - 80 5.1540 2.2338 0.7518 -0.4266 -0.0145 -0.2450 -0.1911 -0.0002 0.0000 -0.0022 0.0380 0.239 - 81 5.4774 2.1058 0.6671 -0.3938 -0.0157 -0.2399 -0.1871 -0.0002 0.0000 -0.0028 0.0367 0.235 - 82 5.7795 1.9862 0.5830 -0.3607 -0.0171 -0.2330 -0.1817 -0.0003 0.0000 -0.0036 0.0349 0.230 - 83 6.0570 1.8764 0.5012 -0.3267 -0.0186 -0.2234 -0.1742 -0.0004 0.0000 -0.0046 0.0324 0.223 - 84 6.3069 1.7776 0.4225 -0.2919 -0.0201 -0.2107 -0.1643 -0.0004 0.0000 -0.0059 0.0293 0.214 - 85 6.5264 1.6907 0.3478 -0.2557 -0.0217 -0.1941 -0.1513 -0.0005 0.0000 -0.0072 0.0255 0.202 - 86 6.7314 1.6096 0.3326 -0.2160 -0.0232 -0.1722 -0.1343 -0.0005 0.0000 -0.0084 0.0209 0.188 - 87 6.9144 1.5372 0.2507 -0.1714 -0.0246 -0.1431 -0.1116 -0.0007 0.0000 -0.0091 0.0156 0.169 - 88 7.0535 1.4822 0.1746 -0.1243 -0.0257 -0.1076 -0.0839 -0.0008 0.0000 -0.0085 0.0103 0.149 - 89 7.1471 1.4451 0.1029 -0.0753 -0.0264 -0.0669 -0.0522 -0.0007 0.0000 -0.0062 0.0057 0.132 - 90 7.1941 1.4265 0.0340 -0.0252 -0.0268 -0.0227 -0.0177 -0.0007 0.0000 -0.0023 0.0018 0.122 + 61 0.0047 4.2713 0.0803 -0.6002 -0.0210 -0.1774 -0.1384 0.0651 0.0000 0.0091 0.0370 0.316 + 62 0.0418 4.2566 0.2392 -0.6919 -0.0215 -0.2082 -0.1624 0.0077 0.0000 0.0088 0.0414 0.304 + 63 0.1156 4.2274 0.3930 -0.6989 -0.0219 -0.2119 -0.1653 0.0039 0.0000 0.0083 0.0415 0.300 + 64 0.2254 4.1839 0.5386 -0.7010 -0.0222 -0.2148 -0.1675 0.0029 0.0000 0.0074 0.0413 0.294 + 65 0.3698 4.1268 0.6730 -0.7012 -0.0223 -0.2179 -0.1699 0.0025 0.0000 0.0063 0.0408 0.287 + 66 0.5474 4.0565 0.7936 -0.7007 -0.0221 -0.2215 -0.1728 0.0021 0.0000 0.0051 0.0404 0.280 + 67 0.7617 3.9717 0.9441 -0.6984 -0.0214 -0.2255 -0.1759 0.0017 0.0000 0.0040 0.0401 0.273 + 68 1.0116 3.8728 1.0344 -0.6948 -0.0201 -0.2301 -0.1795 0.0012 0.0000 0.0029 0.0399 0.266 + 69 1.2891 3.7630 1.1046 -0.6881 -0.0181 -0.2346 -0.1829 0.0009 0.0000 0.0020 0.0399 0.261 + 70 1.5912 3.6435 1.1542 -0.6785 -0.0158 -0.2389 -0.1863 0.0006 0.0000 0.0012 0.0399 0.256 + 71 1.9146 3.5155 1.1831 -0.6659 -0.0134 -0.2430 -0.1895 0.0004 0.0000 0.0006 0.0401 0.253 + 72 2.2558 3.3805 1.1921 -0.6498 -0.0115 -0.2466 -0.1923 0.0002 0.0000 0.0001 0.0402 0.250 + 73 2.6109 3.2400 1.1821 -0.6301 -0.0104 -0.2495 -0.1946 0.0000 0.0000 -0.0003 0.0404 0.249 + 74 2.9762 3.0955 1.1548 -0.6073 -0.0101 -0.2517 -0.1963 -0.0001 0.0000 -0.0006 0.0405 0.247 + 75 3.3476 2.9485 1.1122 -0.5817 -0.0103 -0.2531 -0.1974 -0.0002 0.0000 -0.0008 0.0405 0.246 + 76 3.7210 2.8008 1.0564 -0.5537 -0.0109 -0.2537 -0.1978 -0.0002 0.0000 -0.0010 0.0404 0.245 + 77 4.0924 2.6538 0.9900 -0.5239 -0.0116 -0.2533 -0.1975 -0.0003 0.0000 -0.0012 0.0402 0.244 + 78 4.4577 2.5093 0.9155 -0.4927 -0.0124 -0.2519 -0.1965 -0.0003 0.0000 -0.0014 0.0398 0.243 + 79 4.8128 2.3687 0.8353 -0.4607 -0.0134 -0.2496 -0.1946 -0.0003 0.0000 -0.0018 0.0391 0.241 + 80 5.1540 2.2338 0.7518 -0.4281 -0.0144 -0.2459 -0.1918 -0.0003 0.0000 -0.0022 0.0382 0.239 + 81 5.4774 2.1058 0.6671 -0.3952 -0.0157 -0.2408 -0.1878 -0.0003 0.0000 -0.0028 0.0368 0.235 + 82 5.7795 1.9862 0.5830 -0.3618 -0.0170 -0.2337 -0.1823 -0.0004 0.0000 -0.0036 0.0350 0.230 + 83 6.0570 1.8764 0.5012 -0.3276 -0.0185 -0.2240 -0.1747 -0.0004 0.0000 -0.0047 0.0325 0.223 + 84 6.3069 1.7776 0.4225 -0.2926 -0.0201 -0.2112 -0.1647 -0.0004 0.0000 -0.0059 0.0294 0.214 + 85 6.5264 1.6907 0.3478 -0.2563 -0.0217 -0.1945 -0.1517 -0.0005 0.0000 -0.0072 0.0256 0.202 + 86 6.7314 1.6096 0.3326 -0.2165 -0.0232 -0.1726 -0.1346 -0.0006 0.0000 -0.0084 0.0210 0.188 + 87 6.9144 1.5372 0.2507 -0.1718 -0.0246 -0.1434 -0.1118 -0.0007 0.0000 -0.0091 0.0157 0.169 + 88 7.0535 1.4822 0.1746 -0.1245 -0.0257 -0.1078 -0.0841 -0.0008 0.0000 -0.0085 0.0104 0.149 + 89 7.1471 1.4451 0.1029 -0.0755 -0.0264 -0.0670 -0.0523 -0.0007 0.0000 -0.0062 0.0057 0.132 + 90 7.1941 1.4265 0.0340 -0.0253 -0.0268 -0.0228 -0.0177 -0.0007 0.0000 -0.0023 0.0018 0.122 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02974 Clsurf = -0.00291 - CYsurf = -0.00478 Cmsurf = 0.14270 - CDsurf = 0.00013 Cnsurf = 0.00294 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02990 Clsurf = -0.00292 + CYsurf = -0.00481 Cmsurf = 0.14344 + CDsurf = 0.00013 Cnsurf = 0.00296 CDisurf = 0.00013 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.18132 CDsurf = 0.00079 + CLsurf = -0.18228 CDsurf = 0.00076 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.5971 -0.0211 -0.1765 -0.1377 0.0643 0.0000 0.0091 -0.0368 0.316 - 92 -0.0418 4.2566 0.2392 -0.6876 -0.0216 -0.2069 -0.1614 0.0076 0.0000 0.0087 -0.0411 0.304 - 93 -0.1156 4.2274 0.3930 -0.6946 -0.0220 -0.2106 -0.1643 0.0039 0.0000 0.0082 -0.0413 0.300 - 94 -0.2254 4.1839 0.5386 -0.6965 -0.0223 -0.2135 -0.1665 0.0030 0.0000 0.0074 -0.0410 0.294 - 95 -0.3698 4.1268 0.6730 -0.6968 -0.0224 -0.2165 -0.1689 0.0025 0.0000 0.0063 -0.0406 0.287 - 96 -0.5474 4.0565 0.7936 -0.6960 -0.0221 -0.2200 -0.1716 0.0021 0.0000 0.0051 -0.0402 0.280 - 97 -0.7617 3.9717 0.9441 -0.6943 -0.0215 -0.2242 -0.1749 0.0017 0.0000 0.0040 -0.0399 0.273 - 98 -1.0116 3.8728 1.0344 -0.6901 -0.0202 -0.2286 -0.1782 0.0013 0.0000 0.0029 -0.0397 0.266 - 99 -1.2891 3.7630 1.1046 -0.6837 -0.0182 -0.2331 -0.1818 0.0010 0.0000 0.0020 -0.0396 0.261 - 100 -1.5912 3.6435 1.1542 -0.6742 -0.0159 -0.2374 -0.1851 0.0007 0.0000 0.0012 -0.0397 0.257 - 101 -1.9146 3.5155 1.1831 -0.6616 -0.0135 -0.2414 -0.1883 0.0004 0.0000 0.0006 -0.0398 0.253 - 102 -2.2558 3.3805 1.1921 -0.6459 -0.0116 -0.2451 -0.1912 0.0002 0.0000 0.0001 -0.0400 0.251 - 103 -2.6109 3.2400 1.1821 -0.6265 -0.0106 -0.2481 -0.1935 0.0001 0.0000 -0.0003 -0.0402 0.249 - 104 -2.9762 3.0955 1.1548 -0.6040 -0.0102 -0.2503 -0.1952 -0.0000 0.0000 -0.0006 -0.0403 0.247 - 105 -3.3476 2.9485 1.1122 -0.5786 -0.0104 -0.2518 -0.1964 -0.0002 0.0000 -0.0008 -0.0403 0.246 - 106 -3.7210 2.8008 1.0564 -0.5508 -0.0110 -0.2523 -0.1968 -0.0002 0.0000 -0.0010 -0.0402 0.245 - 107 -4.0924 2.6538 0.9900 -0.5213 -0.0117 -0.2520 -0.1966 -0.0002 0.0000 -0.0012 -0.0400 0.244 - 108 -4.4577 2.5093 0.9155 -0.4904 -0.0125 -0.2508 -0.1956 -0.0002 0.0000 -0.0014 -0.0396 0.243 - 109 -4.8128 2.3687 0.8353 -0.4589 -0.0134 -0.2486 -0.1939 -0.0002 0.0000 -0.0017 -0.0390 0.241 - 110 -5.1540 2.2338 0.7518 -0.4266 -0.0145 -0.2450 -0.1911 -0.0002 0.0000 -0.0022 -0.0380 0.239 - 111 -5.4774 2.1058 0.6671 -0.3938 -0.0157 -0.2399 -0.1871 -0.0002 0.0000 -0.0028 -0.0367 0.235 - 112 -5.7795 1.9862 0.5830 -0.3607 -0.0171 -0.2330 -0.1817 -0.0003 0.0000 -0.0036 -0.0349 0.230 - 113 -6.0570 1.8764 0.5012 -0.3266 -0.0186 -0.2234 -0.1742 -0.0004 0.0000 -0.0046 -0.0324 0.223 - 114 -6.3069 1.7776 0.4225 -0.2919 -0.0201 -0.2107 -0.1643 -0.0004 0.0000 -0.0059 -0.0293 0.214 - 115 -6.5264 1.6907 0.3478 -0.2557 -0.0217 -0.1941 -0.1513 -0.0005 0.0000 -0.0072 -0.0255 0.202 - 116 -6.7314 1.6096 0.3326 -0.2160 -0.0232 -0.1722 -0.1343 -0.0005 0.0000 -0.0084 -0.0209 0.188 - 117 -6.9144 1.5372 0.2507 -0.1714 -0.0246 -0.1431 -0.1116 -0.0007 0.0000 -0.0091 -0.0156 0.169 - 118 -7.0535 1.4822 0.1746 -0.1243 -0.0257 -0.1076 -0.0839 -0.0008 0.0000 -0.0085 -0.0103 0.149 - 119 -7.1471 1.4451 0.1029 -0.0753 -0.0264 -0.0669 -0.0522 -0.0007 0.0000 -0.0062 -0.0057 0.132 - 120 -7.1941 1.4265 0.0340 -0.0252 -0.0268 -0.0227 -0.0177 -0.0007 0.0000 -0.0023 -0.0018 0.122 + 91 -0.0047 4.2713 0.0803 -0.6002 -0.0210 -0.1774 -0.1384 0.0651 0.0000 0.0091 -0.0370 0.316 + 92 -0.0418 4.2566 0.2392 -0.6919 -0.0215 -0.2082 -0.1624 0.0077 0.0000 0.0088 -0.0414 0.304 + 93 -0.1156 4.2274 0.3930 -0.6989 -0.0219 -0.2119 -0.1653 0.0039 0.0000 0.0083 -0.0415 0.300 + 94 -0.2254 4.1839 0.5386 -0.7010 -0.0222 -0.2148 -0.1675 0.0029 0.0000 0.0074 -0.0413 0.294 + 95 -0.3698 4.1268 0.6730 -0.7012 -0.0223 -0.2179 -0.1699 0.0025 0.0000 0.0063 -0.0408 0.287 + 96 -0.5474 4.0565 0.7936 -0.7007 -0.0221 -0.2215 -0.1728 0.0021 0.0000 0.0051 -0.0404 0.280 + 97 -0.7617 3.9717 0.9441 -0.6984 -0.0214 -0.2255 -0.1759 0.0017 0.0000 0.0040 -0.0401 0.273 + 98 -1.0116 3.8728 1.0344 -0.6947 -0.0201 -0.2301 -0.1795 0.0012 0.0000 0.0029 -0.0399 0.266 + 99 -1.2891 3.7630 1.1046 -0.6881 -0.0181 -0.2346 -0.1829 0.0009 0.0000 0.0020 -0.0399 0.261 + 100 -1.5912 3.6435 1.1542 -0.6785 -0.0158 -0.2389 -0.1863 0.0006 0.0000 0.0012 -0.0399 0.256 + 101 -1.9146 3.5155 1.1831 -0.6659 -0.0134 -0.2430 -0.1895 0.0004 0.0000 0.0006 -0.0401 0.253 + 102 -2.2558 3.3805 1.1921 -0.6498 -0.0115 -0.2466 -0.1923 0.0002 0.0000 0.0001 -0.0402 0.250 + 103 -2.6109 3.2400 1.1821 -0.6301 -0.0104 -0.2495 -0.1946 0.0000 0.0000 -0.0003 -0.0404 0.249 + 104 -2.9762 3.0955 1.1548 -0.6073 -0.0101 -0.2517 -0.1963 -0.0001 0.0000 -0.0006 -0.0405 0.247 + 105 -3.3476 2.9485 1.1122 -0.5817 -0.0103 -0.2531 -0.1974 -0.0002 0.0000 -0.0008 -0.0405 0.246 + 106 -3.7210 2.8008 1.0564 -0.5537 -0.0109 -0.2537 -0.1978 -0.0002 0.0000 -0.0010 -0.0404 0.245 + 107 -4.0924 2.6538 0.9900 -0.5239 -0.0116 -0.2533 -0.1975 -0.0003 0.0000 -0.0012 -0.0402 0.244 + 108 -4.4577 2.5093 0.9155 -0.4927 -0.0124 -0.2519 -0.1965 -0.0003 0.0000 -0.0014 -0.0398 0.243 + 109 -4.8128 2.3687 0.8353 -0.4607 -0.0134 -0.2496 -0.1946 -0.0003 0.0000 -0.0018 -0.0391 0.241 + 110 -5.1540 2.2338 0.7518 -0.4281 -0.0144 -0.2459 -0.1918 -0.0003 0.0000 -0.0022 -0.0382 0.239 + 111 -5.4774 2.1058 0.6671 -0.3952 -0.0157 -0.2408 -0.1878 -0.0003 0.0000 -0.0028 -0.0368 0.235 + 112 -5.7795 1.9862 0.5830 -0.3618 -0.0170 -0.2337 -0.1823 -0.0004 0.0000 -0.0036 -0.0350 0.230 + 113 -6.0570 1.8764 0.5012 -0.3276 -0.0185 -0.2240 -0.1747 -0.0004 0.0000 -0.0047 -0.0325 0.223 + 114 -6.3069 1.7776 0.4225 -0.2926 -0.0201 -0.2112 -0.1647 -0.0004 0.0000 -0.0059 -0.0294 0.214 + 115 -6.5264 1.6907 0.3478 -0.2563 -0.0217 -0.1945 -0.1517 -0.0005 0.0000 -0.0072 -0.0256 0.202 + 116 -6.7314 1.6096 0.3326 -0.2165 -0.0232 -0.1726 -0.1346 -0.0006 0.0000 -0.0084 -0.0210 0.188 + 117 -6.9144 1.5372 0.2507 -0.1718 -0.0246 -0.1434 -0.1118 -0.0007 0.0000 -0.0091 -0.0157 0.169 + 118 -7.0535 1.4822 0.1746 -0.1245 -0.0257 -0.1078 -0.0841 -0.0008 0.0000 -0.0085 -0.0104 0.149 + 119 -7.1471 1.4451 0.1029 -0.0755 -0.0264 -0.0670 -0.0523 -0.0007 0.0000 -0.0062 -0.0057 0.132 + 120 -7.1941 1.4265 0.0340 -0.0253 -0.0268 -0.0228 -0.0177 -0.0007 0.0000 -0.0023 -0.0018 0.122 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 - CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = -0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = 0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + Surface area = 34.910358 Ave. chord = 4.190919 + CLsurf = 0.00000 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = -0.00000 + CDsurf = -0.00000 Cnsurf = 0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00000 CDsurf = 0.00000 + CLsurf = 0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.787 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.783 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.768 - 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.754 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.729 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.701 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.664 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.620 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.563 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.495 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.438 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.412 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.386 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.364 + 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.769 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.762 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.752 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.742 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.728 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.703 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.663 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.614 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.562 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.493 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.435 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.404 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.383 + 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.362 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.343 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.327 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.311 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.299 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.292 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.283 - 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.274 - 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.264 - 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.257 - 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.246 - 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.229 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.214 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.196 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.326 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.307 + 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.298 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.286 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.278 + 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.270 + 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.259 + 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.251 + 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.243 + 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.227 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.209 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.191 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.174 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.156 - 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.138 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.154 + 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.143 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00971 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.02449 + CLsurf = -0.00978 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.02442 CDsurf = 0.00022 Cnsurf = 0.00000 CDisurf = 0.00022 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00979 CDsurf = 0.00022 + CLsurf = -0.00986 CDsurf = 0.00022 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.2441 -0.0606 -0.1142 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.210 - 152 -1.3090 31.2096 11.6724 -0.3284 -0.0568 -0.0409 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.171 - 153 -0.9350 34.0626 12.7394 -0.3467 -0.0331 -0.0248 -0.0102 0.0002 0.0000 -0.0017 0.0003 0.086 - 154 -0.5610 36.1619 13.5246 -0.3504 -0.0212 -0.0163 -0.0097 0.0003 0.0000 -0.0022 0.0001 0.026 - 155 -0.1870 37.5332 14.0374 -0.3511 -0.0167 -0.0109 -0.0093 0.0003 0.0000 -0.0024 -0.0000 -0.004 - 156 0.1870 37.5332 14.0374 -0.3511 -0.0167 -0.0109 -0.0093 0.0003 0.0000 -0.0024 -0.0000 -0.004 - 157 0.5610 36.1619 13.5246 -0.3504 -0.0212 -0.0163 -0.0097 0.0003 0.0000 -0.0022 0.0001 0.026 - 158 0.9350 34.0626 12.7394 -0.3467 -0.0331 -0.0248 -0.0102 0.0002 0.0000 -0.0017 0.0003 0.086 - 159 1.3090 31.2096 11.6724 -0.3284 -0.0568 -0.0409 -0.0105 0.0002 0.0000 -0.0008 0.0005 0.171 - 160 1.6830 26.5957 9.9468 -0.2441 -0.0606 -0.1142 -0.0092 0.0001 0.0000 -0.0004 0.0003 0.210 + 151 -1.6830 26.5957 9.9468 -0.2459 -0.0607 -0.1150 -0.0093 0.0001 0.0000 -0.0003 0.0003 0.212 + 152 -1.3090 31.2096 11.6724 -0.3308 -0.0568 -0.0412 -0.0106 0.0002 0.0000 -0.0008 0.0005 0.174 + 153 -0.9350 34.0626 12.7394 -0.3491 -0.0330 -0.0250 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.090 + 154 -0.5610 36.1619 13.5246 -0.3528 -0.0210 -0.0164 -0.0098 0.0003 0.0000 -0.0022 0.0001 0.029 + 155 -0.1870 37.5332 14.0374 -0.3535 -0.0165 -0.0109 -0.0094 0.0003 0.0000 -0.0024 -0.0000 -0.001 + 156 0.1870 37.5332 14.0374 -0.3535 -0.0165 -0.0109 -0.0094 0.0003 0.0000 -0.0024 -0.0000 -0.001 + 157 0.5610 36.1619 13.5246 -0.3528 -0.0210 -0.0164 -0.0098 0.0003 0.0000 -0.0022 0.0001 0.029 + 158 0.9350 34.0626 12.7394 -0.3491 -0.0330 -0.0250 -0.0102 0.0002 0.0000 -0.0016 0.0003 0.090 + 159 1.3090 31.2096 11.6724 -0.3308 -0.0568 -0.0412 -0.0106 0.0002 0.0000 -0.0008 0.0005 0.174 + 160 1.6830 26.5957 9.9468 -0.2459 -0.0607 -0.1150 -0.0093 0.0001 0.0000 -0.0003 0.0003 0.212 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = 0.00000 + CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = -0.00000 Cnsurf = -0.00000 - CDisurf = -0.00000 CDvsurf = 0.00000 + CDsurf = 0.00000 Cnsurf = -0.00000 + CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = 0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.901 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.859 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.851 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.845 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.838 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.816 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.791 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.746 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.582 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.310 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.883 + 162 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.862 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.860 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.852 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.843 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.816 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.802 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.770 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.620 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.320 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_04_02.txt b/regression/scripts/AVL/avl_files/strip_forces_case_04_02.txt index f179fcd001..a4db22aad9 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_04_02.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_04_02.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09706 Clsurf = -0.01568 - CYsurf = -0.00666 Cmsurf = -0.07863 - CDsurf = 0.00135 Cnsurf = 0.00073 - CDisurf = 0.00135 CDvsurf = 0.00000 + CLsurf = 0.09770 Clsurf = -0.01574 + CYsurf = -0.00666 Cmsurf = -0.07898 + CDsurf = 0.00131 Cnsurf = 0.00073 + CDisurf = 0.00131 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.18989 CDsurf = 0.00263 + CLsurf = 0.19114 CDsurf = 0.00255 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 1.6674 0.0492 0.2773 0.2151 0.0846 0.0000 -0.0118 -0.0534 0.305 - 2 0.1025 7.6885 1.0492 1.6109 0.0485 0.2701 0.2095 0.0181 0.0000 -0.0118 -0.0523 0.306 - 3 0.2837 7.5620 1.7073 1.6027 0.0468 0.2733 0.2119 0.0138 0.0000 -0.0110 -0.0522 0.302 - 4 0.5530 7.3741 2.3052 1.5904 0.0443 0.2781 0.2157 0.0122 0.0000 -0.0099 -0.0520 0.296 - 5 0.9075 7.1267 2.8223 1.5664 0.0410 0.2834 0.2198 0.0104 0.0000 -0.0088 -0.0519 0.290 - 6 1.3432 6.8226 3.2414 1.5257 0.0387 0.2883 0.2236 0.0090 0.0000 -0.0080 -0.0520 0.286 - 7 1.8554 6.4651 3.5491 1.4655 0.0406 0.2922 0.2267 0.0075 0.0000 -0.0075 -0.0523 0.283 - 8 2.4386 6.0582 3.7368 1.3793 0.0408 0.2935 0.2277 0.0049 0.0000 -0.0078 -0.0528 0.284 - 9 3.0862 5.6062 3.8005 1.2708 0.0321 0.2923 0.2267 0.0031 0.0000 -0.0089 -0.0534 0.289 - 10 3.7613 5.1351 3.4440 1.1481 0.0218 0.2883 0.2236 0.0012 0.0000 -0.0109 -0.0544 0.299 - 11 4.4532 4.6522 3.3149 1.0183 0.0121 0.2822 0.2189 -0.0005 0.0000 -0.0140 -0.0560 0.314 - 12 5.1831 4.1429 3.0930 0.8815 -0.0008 0.2743 0.2128 -0.0024 0.0000 -0.0184 -0.0583 0.336 - 13 6.0123 3.7903 3.4706 0.7573 -0.0079 0.2433 0.1998 -0.0030 0.0000 -0.0214 -0.0635 0.357 - 14 6.9353 3.6075 3.3775 0.6680 -0.0050 0.2255 0.1852 -0.0021 0.0000 -0.0221 -0.0608 0.369 - 15 7.8737 3.4215 3.2389 0.5961 -0.0029 0.2122 0.1742 -0.0017 0.0000 -0.0222 -0.0585 0.378 - 16 8.8172 3.2345 3.0619 0.5362 -0.0016 0.2019 0.1658 -0.0014 0.0000 -0.0222 -0.0566 0.384 - 17 9.7556 3.0486 2.8543 0.4849 -0.0008 0.1937 0.1591 -0.0012 0.0000 -0.0222 -0.0550 0.389 - 18 10.6786 2.8657 2.6240 0.4402 -0.0003 0.1871 0.1536 -0.0010 0.0000 -0.0221 -0.0538 0.394 - 19 11.5760 2.6879 2.3787 0.4007 0.0002 0.1816 0.1491 -0.0009 0.0000 -0.0220 -0.0527 0.398 - 20 12.4328 2.5181 2.1010 0.3654 0.0007 0.1768 0.1451 -0.0008 0.0000 -0.0219 -0.0517 0.401 - 21 13.2400 2.3582 1.8520 0.3334 0.0013 0.1722 0.1414 -0.0007 0.0000 -0.0217 -0.0507 0.404 - 22 13.9941 2.2087 1.6074 0.3037 0.0022 0.1674 0.1375 -0.0007 0.0000 -0.0215 -0.0496 0.406 - 23 14.6868 2.0715 1.3716 0.2751 0.0034 0.1618 0.1328 -0.0006 0.0000 -0.0211 -0.0482 0.409 - 24 15.3105 1.9479 1.1479 0.2466 0.0051 0.1542 0.1266 -0.0005 0.0000 -0.0204 -0.0462 0.411 - 25 15.8583 1.8393 0.9381 0.2165 0.0071 0.1433 0.1177 -0.0004 0.0000 -0.0194 -0.0434 0.415 - 26 16.3244 1.7470 0.7427 0.1832 0.0094 0.1277 0.1049 -0.0003 0.0000 -0.0182 -0.0394 0.423 - 27 16.6722 1.4928 0.4131 0.1475 0.0121 0.3298 0.0988 -0.0006 0.0000 -0.0151 -0.0186 0.403 - 28 16.9098 1.1466 0.2292 0.1109 0.0164 0.3229 0.0967 -0.0012 0.0000 -0.0102 -0.0161 0.356 - 29 17.0696 0.9138 0.1104 0.0696 0.0205 0.2542 0.0762 -0.0016 0.0000 -0.0039 -0.0107 0.301 - 30 17.1499 0.7967 0.0322 0.0238 0.0226 0.0996 0.0298 -0.0012 0.0000 -0.0003 -0.0036 0.261 + 1 0.0114 7.7520 0.3539 1.6845 0.0491 0.2802 0.2173 0.0846 0.0000 -0.0132 -0.0550 0.311 + 2 0.1025 7.6885 1.0491 1.6271 0.0485 0.2728 0.2116 0.0181 0.0000 -0.0131 -0.0538 0.312 + 3 0.2837 7.5620 1.7073 1.6190 0.0471 0.2760 0.2141 0.0138 0.0000 -0.0124 -0.0537 0.308 + 4 0.5530 7.3741 2.3052 1.6066 0.0448 0.2809 0.2179 0.0118 0.0000 -0.0113 -0.0536 0.302 + 5 0.9075 7.1267 2.8223 1.5829 0.0416 0.2864 0.2221 0.0108 0.0000 -0.0102 -0.0535 0.296 + 6 1.3432 6.8226 3.2414 1.5419 0.0393 0.2914 0.2260 0.0088 0.0000 -0.0093 -0.0536 0.291 + 7 1.8554 6.4651 3.5491 1.4798 0.0413 0.2951 0.2289 0.0064 0.0000 -0.0088 -0.0538 0.289 + 8 2.4386 6.0582 3.7368 1.3943 0.0415 0.2967 0.2302 0.0049 0.0000 -0.0089 -0.0542 0.289 + 9 3.0862 5.6062 3.8005 1.2856 0.0330 0.2957 0.2293 0.0030 0.0000 -0.0098 -0.0547 0.293 + 10 3.7613 5.1351 3.4440 1.1569 0.0225 0.2905 0.2253 0.0012 0.0000 -0.0116 -0.0553 0.301 + 11 4.4532 4.6522 3.3149 1.0259 0.0120 0.2843 0.2205 -0.0005 0.0000 -0.0139 -0.0562 0.313 + 12 5.1831 4.1429 3.0930 0.8853 -0.0015 0.2755 0.2137 -0.0025 0.0000 -0.0173 -0.0577 0.331 + 13 6.0123 3.7903 3.4706 0.7601 -0.0084 0.2442 0.2005 -0.0030 0.0000 -0.0199 -0.0623 0.349 + 14 6.9353 3.6075 3.3775 0.6703 -0.0052 0.2263 0.1858 -0.0022 0.0000 -0.0204 -0.0594 0.360 + 15 7.8737 3.4215 3.2389 0.5981 -0.0031 0.2129 0.1748 -0.0017 0.0000 -0.0205 -0.0571 0.367 + 16 8.8172 3.2345 3.0619 0.5378 -0.0017 0.2025 0.1663 -0.0014 0.0000 -0.0205 -0.0552 0.373 + 17 9.7556 3.0486 2.8543 0.4863 -0.0009 0.1943 0.1595 -0.0012 0.0000 -0.0204 -0.0536 0.378 + 18 10.6786 2.8657 2.6239 0.4414 -0.0003 0.1876 0.1540 -0.0010 0.0000 -0.0203 -0.0523 0.382 + 19 11.5760 2.6879 2.3787 0.4017 0.0001 0.1820 0.1495 -0.0009 0.0000 -0.0203 -0.0512 0.386 + 20 12.4328 2.5181 2.1010 0.3663 0.0006 0.1772 0.1455 -0.0008 0.0000 -0.0201 -0.0502 0.388 + 21 13.2400 2.3582 1.8520 0.3341 0.0013 0.1726 0.1417 -0.0007 0.0000 -0.0200 -0.0492 0.391 + 22 13.9941 2.2087 1.6074 0.3042 0.0022 0.1677 0.1377 -0.0007 0.0000 -0.0197 -0.0481 0.393 + 23 14.6868 2.0715 1.3716 0.2755 0.0034 0.1620 0.1330 -0.0006 0.0000 -0.0193 -0.0467 0.395 + 24 15.3105 1.9479 1.1479 0.2467 0.0050 0.1543 0.1267 -0.0005 0.0000 -0.0186 -0.0447 0.397 + 25 15.8583 1.8393 0.9381 0.2164 0.0070 0.1433 0.1176 -0.0004 0.0000 -0.0176 -0.0418 0.400 + 26 16.3244 1.7470 0.7427 0.1826 0.0091 0.1273 0.1045 -0.0003 0.0000 -0.0164 -0.0378 0.407 + 27 16.6722 1.4928 0.4131 0.1470 0.0117 0.3286 0.0984 -0.0006 0.0000 -0.0137 -0.0179 0.389 + 28 16.9098 1.1466 0.2292 0.1107 0.0164 0.3223 0.0966 -0.0012 0.0000 -0.0091 -0.0156 0.345 + 29 17.0696 0.9138 0.1104 0.0696 0.0207 0.2542 0.0761 -0.0016 0.0000 -0.0032 -0.0104 0.292 + 30 17.1499 0.7967 0.0322 0.0238 0.0234 0.0998 0.0299 -0.0012 0.0000 -0.0001 -0.0036 0.254 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.09706 Clsurf = 0.01568 - CYsurf = 0.00666 Cmsurf = -0.07863 - CDsurf = 0.00135 Cnsurf = -0.00073 - CDisurf = 0.00135 CDvsurf = 0.00000 + CLsurf = 0.09770 Clsurf = 0.01574 + CYsurf = 0.00666 Cmsurf = -0.07898 + CDsurf = 0.00131 Cnsurf = -0.00073 + CDisurf = 0.00131 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.18989 CDsurf = 0.00263 + CLsurf = 0.19114 CDsurf = 0.00255 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 1.6674 0.0492 0.2773 0.2151 0.0846 0.0000 -0.0118 0.0534 0.305 - 32 -0.1025 7.6885 1.0492 1.6109 0.0485 0.2701 0.2095 0.0181 0.0000 -0.0118 0.0523 0.306 - 33 -0.2837 7.5620 1.7073 1.6027 0.0468 0.2733 0.2119 0.0138 0.0000 -0.0110 0.0522 0.302 - 34 -0.5530 7.3741 2.3052 1.5904 0.0443 0.2781 0.2157 0.0122 0.0000 -0.0099 0.0520 0.296 - 35 -0.9075 7.1267 2.8223 1.5664 0.0410 0.2834 0.2198 0.0104 0.0000 -0.0088 0.0519 0.290 - 36 -1.3432 6.8226 3.2414 1.5257 0.0387 0.2883 0.2236 0.0090 0.0000 -0.0080 0.0520 0.286 - 37 -1.8554 6.4651 3.5491 1.4655 0.0406 0.2922 0.2267 0.0075 0.0000 -0.0075 0.0523 0.283 - 38 -2.4386 6.0582 3.7368 1.3793 0.0408 0.2935 0.2277 0.0049 0.0000 -0.0078 0.0528 0.284 - 39 -3.0862 5.6062 3.8005 1.2708 0.0321 0.2923 0.2267 0.0031 0.0000 -0.0089 0.0534 0.289 - 40 -3.7613 5.1351 3.4440 1.1481 0.0218 0.2883 0.2236 0.0012 0.0000 -0.0109 0.0544 0.299 - 41 -4.4532 4.6522 3.3149 1.0183 0.0121 0.2822 0.2189 -0.0005 0.0000 -0.0140 0.0560 0.314 - 42 -5.1831 4.1429 3.0930 0.8815 -0.0008 0.2743 0.2128 -0.0024 0.0000 -0.0184 0.0583 0.336 - 43 -6.0123 3.7903 3.4706 0.7573 -0.0079 0.2433 0.1998 -0.0030 0.0000 -0.0214 0.0635 0.357 - 44 -6.9353 3.6075 3.3775 0.6680 -0.0050 0.2255 0.1852 -0.0021 0.0000 -0.0221 0.0608 0.369 - 45 -7.8737 3.4215 3.2389 0.5961 -0.0029 0.2122 0.1742 -0.0017 0.0000 -0.0222 0.0585 0.378 - 46 -8.8172 3.2345 3.0619 0.5362 -0.0016 0.2019 0.1658 -0.0014 0.0000 -0.0222 0.0566 0.384 - 47 -9.7556 3.0486 2.8543 0.4849 -0.0008 0.1937 0.1591 -0.0012 0.0000 -0.0222 0.0550 0.389 - 48 -10.6786 2.8657 2.6240 0.4402 -0.0003 0.1871 0.1536 -0.0010 0.0000 -0.0221 0.0538 0.394 - 49 -11.5760 2.6879 2.3787 0.4007 0.0002 0.1816 0.1491 -0.0009 0.0000 -0.0220 0.0527 0.398 - 50 -12.4328 2.5181 2.1010 0.3654 0.0007 0.1767 0.1451 -0.0008 0.0000 -0.0219 0.0517 0.401 - 51 -13.2400 2.3582 1.8520 0.3334 0.0013 0.1722 0.1414 -0.0007 0.0000 -0.0217 0.0507 0.404 - 52 -13.9941 2.2087 1.6074 0.3037 0.0022 0.1674 0.1375 -0.0007 0.0000 -0.0215 0.0496 0.406 - 53 -14.6868 2.0715 1.3716 0.2751 0.0034 0.1617 0.1328 -0.0006 0.0000 -0.0211 0.0482 0.409 - 54 -15.3105 1.9479 1.1479 0.2466 0.0051 0.1542 0.1266 -0.0005 0.0000 -0.0204 0.0462 0.411 - 55 -15.8583 1.8393 0.9381 0.2165 0.0071 0.1433 0.1177 -0.0004 0.0000 -0.0194 0.0434 0.415 - 56 -16.3244 1.7470 0.7427 0.1832 0.0094 0.1277 0.1049 -0.0003 0.0000 -0.0182 0.0394 0.423 - 57 -16.6722 1.4928 0.4131 0.1475 0.0121 0.3298 0.0988 -0.0006 0.0000 -0.0151 0.0186 0.403 - 58 -16.9098 1.1466 0.2292 0.1109 0.0164 0.3229 0.0967 -0.0012 0.0000 -0.0102 0.0161 0.356 - 59 -17.0696 0.9138 0.1104 0.0696 0.0205 0.2542 0.0762 -0.0016 0.0000 -0.0039 0.0107 0.301 - 60 -17.1499 0.7967 0.0322 0.0238 0.0226 0.0996 0.0298 -0.0012 0.0000 -0.0003 0.0036 0.261 + 31 -0.0114 7.7520 0.3539 1.6845 0.0491 0.2802 0.2173 0.0846 0.0000 -0.0132 0.0550 0.311 + 32 -0.1025 7.6885 1.0491 1.6271 0.0485 0.2728 0.2116 0.0181 0.0000 -0.0131 0.0538 0.312 + 33 -0.2837 7.5620 1.7073 1.6190 0.0471 0.2760 0.2141 0.0138 0.0000 -0.0124 0.0537 0.308 + 34 -0.5530 7.3741 2.3052 1.6066 0.0448 0.2809 0.2179 0.0118 0.0000 -0.0113 0.0536 0.302 + 35 -0.9075 7.1267 2.8223 1.5829 0.0416 0.2864 0.2221 0.0108 0.0000 -0.0102 0.0535 0.296 + 36 -1.3432 6.8226 3.2414 1.5419 0.0393 0.2914 0.2260 0.0088 0.0000 -0.0093 0.0536 0.291 + 37 -1.8554 6.4651 3.5491 1.4798 0.0413 0.2951 0.2289 0.0064 0.0000 -0.0088 0.0538 0.289 + 38 -2.4386 6.0582 3.7368 1.3943 0.0415 0.2967 0.2302 0.0049 0.0000 -0.0089 0.0542 0.289 + 39 -3.0862 5.6062 3.8005 1.2856 0.0330 0.2957 0.2293 0.0030 0.0000 -0.0098 0.0547 0.293 + 40 -3.7613 5.1351 3.4440 1.1569 0.0225 0.2905 0.2253 0.0012 0.0000 -0.0116 0.0553 0.301 + 41 -4.4532 4.6522 3.3149 1.0259 0.0120 0.2843 0.2205 -0.0005 0.0000 -0.0139 0.0562 0.313 + 42 -5.1831 4.1429 3.0930 0.8853 -0.0015 0.2755 0.2137 -0.0025 0.0000 -0.0173 0.0577 0.331 + 43 -6.0123 3.7903 3.4706 0.7601 -0.0084 0.2442 0.2005 -0.0030 0.0000 -0.0199 0.0623 0.349 + 44 -6.9353 3.6075 3.3775 0.6703 -0.0052 0.2263 0.1858 -0.0022 0.0000 -0.0204 0.0594 0.360 + 45 -7.8737 3.4215 3.2389 0.5981 -0.0031 0.2129 0.1748 -0.0017 0.0000 -0.0205 0.0571 0.367 + 46 -8.8172 3.2345 3.0619 0.5378 -0.0017 0.2025 0.1663 -0.0014 0.0000 -0.0205 0.0552 0.373 + 47 -9.7556 3.0486 2.8543 0.4863 -0.0009 0.1943 0.1595 -0.0012 0.0000 -0.0204 0.0536 0.378 + 48 -10.6786 2.8657 2.6239 0.4414 -0.0003 0.1876 0.1540 -0.0010 0.0000 -0.0203 0.0523 0.382 + 49 -11.5760 2.6879 2.3787 0.4017 0.0001 0.1820 0.1495 -0.0009 0.0000 -0.0203 0.0512 0.386 + 50 -12.4328 2.5181 2.1010 0.3663 0.0006 0.1772 0.1455 -0.0008 0.0000 -0.0201 0.0502 0.388 + 51 -13.2400 2.3582 1.8520 0.3341 0.0013 0.1726 0.1417 -0.0007 0.0000 -0.0200 0.0492 0.391 + 52 -13.9941 2.2087 1.6074 0.3042 0.0022 0.1677 0.1377 -0.0007 0.0000 -0.0197 0.0481 0.393 + 53 -14.6868 2.0715 1.3716 0.2755 0.0034 0.1620 0.1330 -0.0006 0.0000 -0.0193 0.0467 0.395 + 54 -15.3105 1.9479 1.1479 0.2467 0.0050 0.1543 0.1267 -0.0005 0.0000 -0.0186 0.0447 0.397 + 55 -15.8583 1.8393 0.9381 0.2164 0.0070 0.1433 0.1176 -0.0004 0.0000 -0.0176 0.0418 0.400 + 56 -16.3244 1.7470 0.7427 0.1826 0.0091 0.1273 0.1045 -0.0003 0.0000 -0.0164 0.0378 0.407 + 57 -16.6722 1.4928 0.4131 0.1470 0.0117 0.3286 0.0984 -0.0006 0.0000 -0.0137 0.0179 0.389 + 58 -16.9098 1.1466 0.2292 0.1107 0.0164 0.3223 0.0966 -0.0012 0.0000 -0.0091 0.0156 0.345 + 59 -17.0696 0.9138 0.1104 0.0696 0.0207 0.2542 0.0761 -0.0016 0.0000 -0.0032 0.0104 0.292 + 60 -17.1499 0.7967 0.0322 0.0238 0.0234 0.0998 0.0299 -0.0012 0.0000 -0.0001 0.0036 0.254 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01369 Clsurf = 0.00125 - CYsurf = 0.00220 Cmsurf = 0.06543 - CDsurf = -0.00020 Cnsurf = -0.00132 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01384 Clsurf = 0.00127 + CYsurf = 0.00223 Cmsurf = 0.06615 + CDsurf = -0.00020 Cnsurf = -0.00133 CDisurf = -0.00020 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.08343 CDsurf = -0.00118 + CLsurf = -0.08435 CDsurf = -0.00120 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.3276 0.0114 -0.0989 -0.0767 0.0154 0.0000 0.0039 0.0195 0.301 - 62 0.0418 4.2566 0.2392 -0.3510 0.0111 -0.1064 -0.0825 0.0005 0.0000 0.0038 0.0206 0.296 - 63 0.1156 4.2274 0.3930 -0.3528 0.0108 -0.1076 -0.0835 -0.0005 0.0000 0.0035 0.0206 0.292 - 64 0.2254 4.1839 0.5386 -0.3532 0.0104 -0.1089 -0.0844 -0.0007 0.0000 0.0031 0.0204 0.286 - 65 0.3698 4.1268 0.6730 -0.3530 0.0101 -0.1103 -0.0855 -0.0009 0.0000 0.0025 0.0202 0.279 - 66 0.5474 4.0565 0.7936 -0.3522 0.0098 -0.1120 -0.0868 -0.0010 0.0000 0.0019 0.0199 0.272 - 67 0.7617 3.9717 0.9441 -0.3507 0.0096 -0.1139 -0.0883 -0.0012 0.0000 0.0013 0.0197 0.265 - 68 1.0116 3.8728 1.0344 -0.3476 0.0097 -0.1158 -0.0898 -0.0013 0.0000 0.0007 0.0196 0.258 - 69 1.2891 3.7630 1.1046 -0.3431 0.0099 -0.1176 -0.0912 -0.0014 0.0000 0.0003 0.0195 0.253 - 70 1.5912 3.6435 1.1542 -0.3364 0.0103 -0.1191 -0.0923 -0.0015 0.0000 -0.0001 0.0194 0.249 - 71 1.9146 3.5155 1.1831 -0.3276 0.0108 -0.1202 -0.0932 -0.0016 0.0000 -0.0005 0.0193 0.245 - 72 2.2558 3.3805 1.1921 -0.3164 0.0110 -0.1207 -0.0936 -0.0016 0.0000 -0.0007 0.0192 0.243 - 73 2.6109 3.2400 1.1821 -0.3028 0.0108 -0.1206 -0.0935 -0.0016 0.0000 -0.0009 0.0190 0.241 - 74 2.9762 3.0955 1.1548 -0.2871 0.0103 -0.1196 -0.0927 -0.0016 0.0000 -0.0010 0.0187 0.239 - 75 3.3476 2.9485 1.1122 -0.2694 0.0096 -0.1179 -0.0914 -0.0016 0.0000 -0.0010 0.0184 0.239 - 76 3.7210 2.8008 1.0564 -0.2504 0.0088 -0.1153 -0.0894 -0.0015 0.0000 -0.0011 0.0180 0.238 - 77 4.0924 2.6538 0.9900 -0.2306 0.0081 -0.1121 -0.0869 -0.0014 0.0000 -0.0011 0.0174 0.238 - 78 4.4577 2.5093 0.9155 -0.2105 0.0074 -0.1082 -0.0839 -0.0013 0.0000 -0.0011 0.0168 0.237 - 79 4.8128 2.3687 0.8353 -0.1907 0.0067 -0.1038 -0.0805 -0.0012 0.0000 -0.0011 0.0161 0.236 - 80 5.1540 2.2338 0.7518 -0.1714 0.0061 -0.0990 -0.0767 -0.0011 0.0000 -0.0011 0.0152 0.235 - 81 5.4774 2.1058 0.6671 -0.1529 0.0055 -0.0936 -0.0726 -0.0010 0.0000 -0.0013 0.0143 0.233 - 82 5.7795 1.9862 0.5830 -0.1354 0.0049 -0.0879 -0.0682 -0.0009 0.0000 -0.0014 0.0132 0.229 - 83 6.0570 1.8764 0.5012 -0.1188 0.0043 -0.0817 -0.0633 -0.0008 0.0000 -0.0017 0.0119 0.223 - 84 6.3069 1.7776 0.4225 -0.1031 0.0037 -0.0748 -0.0580 -0.0007 0.0000 -0.0020 0.0106 0.216 - 85 6.5264 1.6907 0.3478 -0.0879 0.0031 -0.0671 -0.0520 -0.0007 0.0000 -0.0023 0.0090 0.205 - 86 6.7314 1.6096 0.3326 -0.0725 0.0026 -0.0581 -0.0450 -0.0006 0.0000 -0.0026 0.0073 0.192 - 87 6.9144 1.5372 0.2507 -0.0563 0.0021 -0.0472 -0.0366 -0.0005 0.0000 -0.0028 0.0054 0.174 - 88 7.0535 1.4822 0.1746 -0.0402 0.0017 -0.0350 -0.0271 -0.0004 0.0000 -0.0026 0.0036 0.156 - 89 7.1471 1.4451 0.1029 -0.0241 0.0015 -0.0215 -0.0167 -0.0002 0.0000 -0.0018 0.0020 0.140 - 90 7.1941 1.4265 0.0340 -0.0080 0.0013 -0.0073 -0.0056 -0.0001 0.0000 -0.0007 0.0006 0.130 + 61 0.0047 4.2713 0.0803 -0.3313 0.0115 -0.1000 -0.0776 0.0158 0.0000 0.0040 0.0197 0.301 + 62 0.0418 4.2566 0.2392 -0.3553 0.0112 -0.1077 -0.0835 0.0005 0.0000 0.0038 0.0208 0.296 + 63 0.1156 4.2274 0.3930 -0.3572 0.0109 -0.1090 -0.0845 -0.0005 0.0000 0.0036 0.0208 0.292 + 64 0.2254 4.1839 0.5386 -0.3576 0.0105 -0.1102 -0.0855 -0.0008 0.0000 0.0031 0.0207 0.286 + 65 0.3698 4.1268 0.6730 -0.3574 0.0102 -0.1117 -0.0866 -0.0009 0.0000 0.0025 0.0204 0.279 + 66 0.5474 4.0565 0.7936 -0.3567 0.0099 -0.1134 -0.0879 -0.0011 0.0000 0.0019 0.0202 0.272 + 67 0.7617 3.9717 0.9441 -0.3549 0.0097 -0.1153 -0.0894 -0.0012 0.0000 0.0013 0.0200 0.265 + 68 1.0116 3.8728 1.0344 -0.3520 0.0098 -0.1172 -0.0909 -0.0013 0.0000 0.0008 0.0198 0.258 + 69 1.2891 3.7630 1.1046 -0.3473 0.0100 -0.1191 -0.0923 -0.0015 0.0000 0.0003 0.0197 0.253 + 70 1.5912 3.6435 1.1542 -0.3406 0.0105 -0.1206 -0.0935 -0.0015 0.0000 -0.0001 0.0196 0.248 + 71 1.9146 3.5155 1.1831 -0.3316 0.0109 -0.1217 -0.0943 -0.0016 0.0000 -0.0005 0.0195 0.245 + 72 2.2558 3.3805 1.1921 -0.3203 0.0111 -0.1222 -0.0947 -0.0017 0.0000 -0.0007 0.0194 0.242 + 73 2.6109 3.2400 1.1821 -0.3064 0.0109 -0.1220 -0.0946 -0.0017 0.0000 -0.0009 0.0192 0.241 + 74 2.9762 3.0955 1.1548 -0.2904 0.0104 -0.1210 -0.0938 -0.0017 0.0000 -0.0010 0.0190 0.239 + 75 3.3476 2.9485 1.1122 -0.2725 0.0097 -0.1192 -0.0924 -0.0016 0.0000 -0.0011 0.0186 0.239 + 76 3.7210 2.8008 1.0564 -0.2532 0.0089 -0.1166 -0.0904 -0.0015 0.0000 -0.0011 0.0182 0.238 + 77 4.0924 2.6538 0.9900 -0.2330 0.0082 -0.1133 -0.0878 -0.0015 0.0000 -0.0011 0.0176 0.238 + 78 4.4577 2.5093 0.9155 -0.2126 0.0074 -0.1093 -0.0847 -0.0014 0.0000 -0.0011 0.0170 0.237 + 79 4.8128 2.3687 0.8353 -0.1925 0.0068 -0.1048 -0.0812 -0.0012 0.0000 -0.0011 0.0162 0.236 + 80 5.1540 2.2338 0.7518 -0.1729 0.0061 -0.0998 -0.0774 -0.0011 0.0000 -0.0012 0.0153 0.235 + 81 5.4774 2.1058 0.6671 -0.1542 0.0055 -0.0944 -0.0732 -0.0010 0.0000 -0.0013 0.0144 0.233 + 82 5.7795 1.9862 0.5830 -0.1365 0.0049 -0.0886 -0.0687 -0.0009 0.0000 -0.0014 0.0133 0.229 + 83 6.0570 1.8764 0.5012 -0.1197 0.0043 -0.0823 -0.0638 -0.0008 0.0000 -0.0017 0.0120 0.224 + 84 6.3069 1.7776 0.4225 -0.1038 0.0037 -0.0753 -0.0584 -0.0007 0.0000 -0.0020 0.0106 0.216 + 85 6.5264 1.6907 0.3478 -0.0885 0.0031 -0.0675 -0.0523 -0.0007 0.0000 -0.0023 0.0091 0.205 + 86 6.7314 1.6096 0.3326 -0.0729 0.0026 -0.0585 -0.0453 -0.0006 0.0000 -0.0026 0.0073 0.192 + 87 6.9144 1.5372 0.2507 -0.0566 0.0021 -0.0475 -0.0368 -0.0005 0.0000 -0.0028 0.0054 0.175 + 88 7.0535 1.4822 0.1746 -0.0404 0.0018 -0.0352 -0.0273 -0.0004 0.0000 -0.0026 0.0036 0.156 + 89 7.1471 1.4451 0.1029 -0.0242 0.0015 -0.0216 -0.0168 -0.0002 0.0000 -0.0018 0.0020 0.140 + 90 7.1941 1.4265 0.0340 -0.0081 0.0014 -0.0073 -0.0057 -0.0001 0.0000 -0.0007 0.0006 0.130 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01368 Clsurf = -0.00125 - CYsurf = -0.00220 Cmsurf = 0.06543 - CDsurf = -0.00020 Cnsurf = 0.00132 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01384 Clsurf = -0.00127 + CYsurf = -0.00223 Cmsurf = 0.06615 + CDsurf = -0.00020 Cnsurf = 0.00133 CDisurf = -0.00020 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.08342 CDsurf = -0.00118 + CLsurf = -0.08435 CDsurf = -0.00120 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.3276 0.0114 -0.0989 -0.0767 0.0154 0.0000 0.0039 -0.0195 0.301 - 92 -0.0418 4.2566 0.2392 -0.3510 0.0111 -0.1064 -0.0825 0.0005 0.0000 0.0038 -0.0206 0.296 - 93 -0.1156 4.2274 0.3930 -0.3528 0.0108 -0.1076 -0.0835 -0.0005 0.0000 0.0035 -0.0206 0.292 - 94 -0.2254 4.1839 0.5386 -0.3532 0.0104 -0.1089 -0.0844 -0.0007 0.0000 0.0031 -0.0204 0.286 - 95 -0.3698 4.1268 0.6730 -0.3530 0.0101 -0.1103 -0.0855 -0.0009 0.0000 0.0025 -0.0202 0.279 - 96 -0.5474 4.0565 0.7936 -0.3522 0.0098 -0.1120 -0.0868 -0.0010 0.0000 0.0019 -0.0199 0.272 - 97 -0.7617 3.9717 0.9441 -0.3506 0.0096 -0.1139 -0.0883 -0.0012 0.0000 0.0013 -0.0197 0.265 - 98 -1.0116 3.8728 1.0344 -0.3476 0.0097 -0.1158 -0.0898 -0.0013 0.0000 0.0007 -0.0196 0.258 - 99 -1.2891 3.7630 1.1046 -0.3431 0.0099 -0.1176 -0.0912 -0.0014 0.0000 0.0003 -0.0195 0.253 - 100 -1.5912 3.6435 1.1542 -0.3364 0.0103 -0.1191 -0.0923 -0.0015 0.0000 -0.0001 -0.0194 0.249 - 101 -1.9146 3.5155 1.1831 -0.3276 0.0108 -0.1202 -0.0932 -0.0016 0.0000 -0.0005 -0.0193 0.245 - 102 -2.2558 3.3805 1.1921 -0.3164 0.0110 -0.1207 -0.0936 -0.0016 0.0000 -0.0007 -0.0192 0.243 - 103 -2.6109 3.2400 1.1821 -0.3028 0.0108 -0.1206 -0.0935 -0.0016 0.0000 -0.0009 -0.0190 0.241 - 104 -2.9762 3.0955 1.1548 -0.2871 0.0103 -0.1196 -0.0927 -0.0016 0.0000 -0.0010 -0.0187 0.239 - 105 -3.3476 2.9485 1.1122 -0.2694 0.0096 -0.1179 -0.0914 -0.0016 0.0000 -0.0010 -0.0184 0.239 - 106 -3.7210 2.8008 1.0564 -0.2504 0.0088 -0.1153 -0.0894 -0.0015 0.0000 -0.0011 -0.0180 0.238 - 107 -4.0924 2.6538 0.9900 -0.2306 0.0081 -0.1121 -0.0869 -0.0014 0.0000 -0.0011 -0.0174 0.238 - 108 -4.4577 2.5093 0.9155 -0.2105 0.0074 -0.1082 -0.0839 -0.0013 0.0000 -0.0011 -0.0168 0.237 - 109 -4.8128 2.3687 0.8353 -0.1907 0.0067 -0.1038 -0.0805 -0.0012 0.0000 -0.0011 -0.0161 0.236 - 110 -5.1540 2.2338 0.7518 -0.1714 0.0061 -0.0990 -0.0767 -0.0011 0.0000 -0.0011 -0.0152 0.235 - 111 -5.4774 2.1058 0.6671 -0.1529 0.0055 -0.0936 -0.0726 -0.0010 0.0000 -0.0013 -0.0143 0.233 - 112 -5.7795 1.9862 0.5830 -0.1354 0.0049 -0.0879 -0.0682 -0.0009 0.0000 -0.0014 -0.0132 0.229 - 113 -6.0570 1.8764 0.5012 -0.1188 0.0043 -0.0817 -0.0633 -0.0008 0.0000 -0.0017 -0.0119 0.223 - 114 -6.3069 1.7776 0.4225 -0.1031 0.0037 -0.0748 -0.0580 -0.0007 0.0000 -0.0020 -0.0106 0.216 - 115 -6.5264 1.6907 0.3478 -0.0879 0.0031 -0.0671 -0.0520 -0.0007 0.0000 -0.0023 -0.0090 0.205 - 116 -6.7314 1.6096 0.3326 -0.0725 0.0026 -0.0581 -0.0450 -0.0006 0.0000 -0.0026 -0.0073 0.192 - 117 -6.9144 1.5372 0.2507 -0.0563 0.0021 -0.0472 -0.0366 -0.0005 0.0000 -0.0028 -0.0054 0.174 - 118 -7.0535 1.4822 0.1746 -0.0402 0.0017 -0.0350 -0.0271 -0.0004 0.0000 -0.0026 -0.0036 0.156 - 119 -7.1471 1.4451 0.1029 -0.0241 0.0015 -0.0215 -0.0167 -0.0002 0.0000 -0.0018 -0.0020 0.140 - 120 -7.1941 1.4265 0.0340 -0.0080 0.0013 -0.0073 -0.0056 -0.0001 0.0000 -0.0007 -0.0006 0.130 + 91 -0.0047 4.2713 0.0803 -0.3313 0.0115 -0.1000 -0.0776 0.0158 0.0000 0.0040 -0.0197 0.301 + 92 -0.0418 4.2566 0.2392 -0.3553 0.0112 -0.1077 -0.0835 0.0005 0.0000 0.0038 -0.0208 0.296 + 93 -0.1156 4.2274 0.3930 -0.3572 0.0109 -0.1090 -0.0845 -0.0005 0.0000 0.0036 -0.0208 0.292 + 94 -0.2254 4.1839 0.5386 -0.3576 0.0105 -0.1102 -0.0855 -0.0008 0.0000 0.0031 -0.0207 0.286 + 95 -0.3698 4.1268 0.6730 -0.3574 0.0102 -0.1117 -0.0866 -0.0009 0.0000 0.0025 -0.0204 0.279 + 96 -0.5474 4.0565 0.7936 -0.3567 0.0099 -0.1134 -0.0879 -0.0011 0.0000 0.0019 -0.0202 0.272 + 97 -0.7617 3.9717 0.9441 -0.3549 0.0097 -0.1153 -0.0894 -0.0012 0.0000 0.0013 -0.0200 0.265 + 98 -1.0116 3.8728 1.0344 -0.3520 0.0098 -0.1172 -0.0909 -0.0013 0.0000 0.0008 -0.0198 0.258 + 99 -1.2891 3.7630 1.1046 -0.3473 0.0100 -0.1191 -0.0923 -0.0015 0.0000 0.0003 -0.0197 0.253 + 100 -1.5912 3.6435 1.1542 -0.3406 0.0105 -0.1206 -0.0935 -0.0015 0.0000 -0.0001 -0.0196 0.248 + 101 -1.9146 3.5155 1.1831 -0.3316 0.0109 -0.1217 -0.0943 -0.0016 0.0000 -0.0005 -0.0195 0.245 + 102 -2.2558 3.3805 1.1921 -0.3203 0.0111 -0.1222 -0.0947 -0.0017 0.0000 -0.0007 -0.0194 0.242 + 103 -2.6109 3.2400 1.1821 -0.3064 0.0109 -0.1220 -0.0946 -0.0017 0.0000 -0.0009 -0.0192 0.241 + 104 -2.9762 3.0955 1.1548 -0.2904 0.0104 -0.1210 -0.0938 -0.0017 0.0000 -0.0010 -0.0190 0.239 + 105 -3.3476 2.9485 1.1122 -0.2725 0.0097 -0.1192 -0.0924 -0.0016 0.0000 -0.0011 -0.0186 0.239 + 106 -3.7210 2.8008 1.0564 -0.2532 0.0089 -0.1166 -0.0904 -0.0015 0.0000 -0.0011 -0.0182 0.238 + 107 -4.0924 2.6538 0.9900 -0.2330 0.0082 -0.1133 -0.0878 -0.0015 0.0000 -0.0011 -0.0176 0.238 + 108 -4.4577 2.5093 0.9155 -0.2126 0.0074 -0.1093 -0.0847 -0.0014 0.0000 -0.0011 -0.0170 0.237 + 109 -4.8128 2.3687 0.8353 -0.1925 0.0068 -0.1048 -0.0812 -0.0012 0.0000 -0.0011 -0.0162 0.236 + 110 -5.1540 2.2338 0.7518 -0.1729 0.0061 -0.0998 -0.0774 -0.0011 0.0000 -0.0012 -0.0153 0.235 + 111 -5.4774 2.1058 0.6671 -0.1542 0.0055 -0.0944 -0.0732 -0.0010 0.0000 -0.0013 -0.0144 0.233 + 112 -5.7795 1.9862 0.5830 -0.1365 0.0049 -0.0886 -0.0687 -0.0009 0.0000 -0.0014 -0.0133 0.229 + 113 -6.0570 1.8764 0.5012 -0.1197 0.0043 -0.0823 -0.0638 -0.0008 0.0000 -0.0017 -0.0120 0.224 + 114 -6.3069 1.7776 0.4225 -0.1038 0.0037 -0.0753 -0.0584 -0.0007 0.0000 -0.0020 -0.0106 0.216 + 115 -6.5264 1.6907 0.3478 -0.0885 0.0031 -0.0675 -0.0523 -0.0007 0.0000 -0.0023 -0.0091 0.205 + 116 -6.7314 1.6096 0.3326 -0.0729 0.0026 -0.0585 -0.0453 -0.0006 0.0000 -0.0026 -0.0073 0.192 + 117 -6.9144 1.5372 0.2507 -0.0566 0.0021 -0.0475 -0.0368 -0.0005 0.0000 -0.0028 -0.0054 0.175 + 118 -7.0535 1.4822 0.1746 -0.0404 0.0018 -0.0352 -0.0273 -0.0004 0.0000 -0.0026 -0.0036 0.156 + 119 -7.1471 1.4451 0.1029 -0.0242 0.0015 -0.0216 -0.0168 -0.0002 0.0000 -0.0018 -0.0020 0.140 + 120 -7.1941 1.4265 0.0340 -0.0081 0.0014 -0.0073 -0.0057 -0.0001 0.0000 -0.0007 -0.0006 0.130 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = -0.00000 CYsurf = -0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = 0.00000 @@ -199,83 +199,83 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 124 0.0000 9.1281 1.8040 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.905 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.680 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.468 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.279 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.151 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.091 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.078 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.038 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.045 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.058 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.130 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.348 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.788 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.394 - 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.160 - 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.063 - 145 0.0000 1.5493 0.3400 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.002 - 146 0.0000 1.4342 0.2622 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.036 - 147 0.0000 1.3407 0.1933 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.042 - 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.008 - 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.051 - 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.031 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.811 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.718 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.596 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.639 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.716 + 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.749 + 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 139 0.0000 2.6103 0.9908 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.918 + 140 0.0000 2.3983 0.8670 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.400 + 141 0.0000 2.1977 0.7464 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.189 + 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.036 + 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.109 + 144 0.0000 1.6847 0.4276 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.095 + 145 0.0000 1.5493 0.3400 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.108 + 146 0.0000 1.4342 0.2622 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.151 + 147 0.0000 1.3407 0.1933 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.110 + 148 0.0000 1.2696 0.1322 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.064 + 149 0.0000 1.2218 0.0769 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.061 + 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.016 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00509 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.00420 - CDsurf = 0.00002 Cnsurf = 0.00000 - CDisurf = 0.00002 CDvsurf = 0.00000 + CLsurf = -0.00516 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00413 + CDsurf = 0.00003 Cnsurf = 0.00000 + CDisurf = 0.00003 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00513 CDsurf = 0.00002 + CLsurf = -0.00520 CDsurf = 0.00003 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.1345 -0.0067 -0.0638 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.404 - 152 -1.3090 31.2096 11.6724 -0.1753 -0.0006 -0.0219 -0.0056 -0.0000 0.0000 0.0006 0.0005 0.365 - 153 -0.9350 34.0626 12.7394 -0.1811 0.0144 -0.0130 -0.0053 0.0001 0.0000 0.0002 0.0005 0.296 - 154 -0.5610 36.1619 13.5246 -0.1801 0.0225 -0.0084 -0.0050 0.0001 0.0000 -0.0000 0.0006 0.247 - 155 -0.1870 37.5332 14.0374 -0.1789 0.0261 -0.0055 -0.0048 0.0001 0.0000 -0.0001 0.0007 0.223 - 156 0.1870 37.5332 14.0374 -0.1789 0.0261 -0.0055 -0.0048 0.0001 0.0000 -0.0001 0.0007 0.223 - 157 0.5610 36.1619 13.5246 -0.1801 0.0225 -0.0084 -0.0050 0.0001 0.0000 -0.0000 0.0006 0.247 - 158 0.9350 34.0626 12.7394 -0.1811 0.0144 -0.0130 -0.0053 0.0001 0.0000 0.0002 0.0005 0.296 - 159 1.3090 31.2096 11.6724 -0.1753 -0.0006 -0.0219 -0.0056 -0.0000 0.0000 0.0006 0.0005 0.365 - 160 1.6830 26.5957 9.9468 -0.1345 -0.0067 -0.0638 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.404 + 151 -1.6830 26.5957 9.9468 -0.1363 -0.0067 -0.0646 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.407 + 152 -1.3090 31.2096 11.6724 -0.1777 -0.0006 -0.0222 -0.0057 0.0000 0.0000 0.0007 0.0005 0.368 + 153 -0.9350 34.0626 12.7394 -0.1836 0.0145 -0.0132 -0.0054 0.0001 0.0000 0.0003 0.0005 0.300 + 154 -0.5610 36.1619 13.5246 -0.1826 0.0227 -0.0085 -0.0051 0.0001 0.0000 0.0000 0.0006 0.251 + 155 -0.1870 37.5332 14.0374 -0.1814 0.0263 -0.0056 -0.0048 0.0001 0.0000 -0.0001 0.0008 0.226 + 156 0.1870 37.5332 14.0374 -0.1814 0.0263 -0.0056 -0.0048 0.0001 0.0000 -0.0001 0.0008 0.226 + 157 0.5610 36.1619 13.5246 -0.1826 0.0227 -0.0085 -0.0051 0.0001 0.0000 0.0000 0.0006 0.251 + 158 0.9350 34.0626 12.7394 -0.1836 0.0145 -0.0132 -0.0054 0.0001 0.0000 0.0003 0.0005 0.300 + 159 1.3090 31.2096 11.6724 -0.1777 -0.0006 -0.0222 -0.0057 0.0000 0.0000 0.0007 0.0005 0.368 + 160 1.6830 26.5957 9.9468 -0.1363 -0.0067 -0.0646 -0.0051 -0.0001 0.0000 0.0008 0.0003 0.407 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = -0.00000 Cnsurf = -0.00000 - CDisurf = -0.00000 CDvsurf = 0.00000 + CLsurf = 0.00000 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 + CDsurf = 0.00000 Cnsurf = -0.00000 + CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = 0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.997 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.717 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.688 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.677 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.666 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.652 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.623 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.588 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.518 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.480 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.274 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.703 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.696 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.686 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.665 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.650 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.636 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.599 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.534 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.482 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_04_03.txt b/regression/scripts/AVL/avl_files/strip_forces_case_04_03.txt index 0353315aa7..97c1b05fad 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_04_03.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_04_03.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.18464 Clsurf = -0.03390 - CYsurf = -0.01243 Cmsurf = -0.16065 - CDsurf = 0.00352 Cnsurf = 0.00020 - CDisurf = 0.00352 CDvsurf = 0.00000 + CLsurf = 0.18525 Clsurf = -0.03396 + CYsurf = -0.01236 Cmsurf = -0.16098 + CDsurf = 0.00340 Cnsurf = 0.00019 + CDisurf = 0.00340 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.36121 CDsurf = 0.00687 + CLsurf = 0.36240 CDsurf = 0.00663 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 2.6323 0.0858 0.4297 0.3329 0.1974 0.0000 -0.0189 -0.0848 0.307 - 2 0.1025 7.6885 1.0492 2.4987 0.0851 0.4180 0.3238 0.0400 0.0000 -0.0190 -0.0819 0.309 - 3 0.2837 7.5620 1.7073 2.4844 0.0836 0.4230 0.3277 0.0300 0.0000 -0.0177 -0.0816 0.304 - 4 0.5530 7.3741 2.3052 2.4699 0.0809 0.4315 0.3342 0.0266 0.0000 -0.0159 -0.0814 0.298 - 5 0.9075 7.1267 2.8223 2.4431 0.0769 0.4418 0.3422 0.0232 0.0000 -0.0139 -0.0814 0.291 - 6 1.3432 6.8226 3.2414 2.3977 0.0717 0.4530 0.3509 0.0207 0.0000 -0.0122 -0.0818 0.285 - 7 1.8554 6.4651 3.5491 2.3313 0.0658 0.4650 0.3602 0.0179 0.0000 -0.0110 -0.0827 0.281 - 8 2.4386 6.0582 3.7368 2.2322 0.0587 0.4754 0.3682 0.0126 0.0000 -0.0107 -0.0840 0.279 - 9 3.0862 5.6062 3.8005 2.1085 0.0485 0.4854 0.3760 0.0094 0.0000 -0.0113 -0.0861 0.280 - 10 3.7613 5.1351 3.4440 1.9663 0.0378 0.4944 0.3829 0.0057 0.0000 -0.0130 -0.0888 0.284 - 11 4.4532 4.6522 3.3149 1.8135 0.0268 0.5035 0.3900 0.0018 0.0000 -0.0159 -0.0926 0.291 - 12 5.1831 4.1429 3.0930 1.6504 0.0115 0.5148 0.3987 -0.0029 0.0000 -0.0197 -0.0975 0.299 - 13 6.0123 3.7903 3.4706 1.4952 0.0021 0.4823 0.3949 -0.0047 0.0000 -0.0215 -0.1072 0.305 - 14 6.9353 3.6075 3.3775 1.3789 0.0037 0.4673 0.3826 -0.0033 0.0000 -0.0220 -0.1049 0.308 - 15 7.8737 3.4215 3.2389 1.2796 0.0041 0.4572 0.3743 -0.0027 0.0000 -0.0221 -0.1031 0.309 - 16 8.8172 3.2345 3.0619 1.1910 0.0044 0.4501 0.3685 -0.0024 0.0000 -0.0220 -0.1017 0.310 - 17 9.7556 3.0486 2.8543 1.1097 0.0049 0.4449 0.3643 -0.0022 0.0000 -0.0219 -0.1007 0.310 - 18 10.6786 2.8657 2.6240 1.0338 0.0056 0.4410 0.3610 -0.0020 0.0000 -0.0217 -0.0998 0.310 - 19 11.5760 2.6879 2.3787 0.9621 0.0064 0.4375 0.3582 -0.0020 0.0000 -0.0215 -0.0990 0.310 - 20 12.4328 2.5181 2.1010 0.8939 0.0075 0.4339 0.3553 -0.0019 0.0000 -0.0212 -0.0981 0.310 - 21 13.2400 2.3582 1.8520 0.8280 0.0091 0.4292 0.3514 -0.0019 0.0000 -0.0207 -0.0968 0.309 - 22 13.9941 2.2087 1.6074 0.7630 0.0113 0.4223 0.3457 -0.0018 0.0000 -0.0200 -0.0949 0.308 - 23 14.6868 2.0715 1.3716 0.6970 0.0142 0.4113 0.3367 -0.0017 0.0000 -0.0189 -0.0920 0.306 - 24 15.3105 1.9479 1.1479 0.6273 0.0180 0.3936 0.3223 -0.0015 0.0000 -0.0173 -0.0873 0.304 - 25 15.8583 1.8393 0.9381 0.5504 0.0223 0.3657 0.2994 -0.0011 0.0000 -0.0154 -0.0805 0.302 - 26 16.3244 1.7470 0.7427 0.4635 0.0269 0.3242 0.2655 -0.0001 0.0000 -0.0151 -0.0726 0.307 - 27 16.6722 1.4928 0.4131 0.3700 0.0319 0.8345 0.2482 -0.0040 0.0000 -0.0137 -0.0359 0.305 - 28 16.9098 1.1466 0.2292 0.2749 0.0393 0.8076 0.2402 -0.0085 0.0000 -0.0030 -0.0300 0.262 - 29 17.0696 0.9138 0.1104 0.1703 0.0455 0.6285 0.1869 -0.0119 0.0000 0.0083 -0.0184 0.206 - 30 17.1499 0.7967 0.0322 0.0577 0.0486 0.2449 0.0728 -0.0082 0.0000 0.0069 -0.0054 0.155 + 1 0.0114 7.7520 0.3539 2.6499 0.0857 0.4327 0.3351 0.1977 0.0000 -0.0204 -0.0865 0.311 + 2 0.1025 7.6885 1.0491 2.5149 0.0851 0.4207 0.3259 0.0400 0.0000 -0.0203 -0.0834 0.312 + 3 0.2837 7.5620 1.7073 2.5007 0.0839 0.4258 0.3298 0.0300 0.0000 -0.0191 -0.0831 0.308 + 4 0.5530 7.3741 2.3052 2.4857 0.0814 0.4343 0.3364 0.0258 0.0000 -0.0173 -0.0830 0.301 + 5 0.9075 7.1267 2.8223 2.4594 0.0775 0.4447 0.3445 0.0240 0.0000 -0.0153 -0.0830 0.294 + 6 1.3432 6.8226 3.2414 2.4135 0.0723 0.4560 0.3533 0.0201 0.0000 -0.0136 -0.0833 0.288 + 7 1.8554 6.4651 3.5491 2.3435 0.0664 0.4675 0.3622 0.0151 0.0000 -0.0124 -0.0841 0.284 + 8 2.4386 6.0582 3.7368 2.2473 0.0594 0.4786 0.3707 0.0125 0.0000 -0.0118 -0.0854 0.282 + 9 3.0862 5.6062 3.8005 2.1247 0.0495 0.4891 0.3789 0.0091 0.0000 -0.0122 -0.0874 0.282 + 10 3.7613 5.1351 3.4440 1.9706 0.0385 0.4955 0.3838 0.0054 0.0000 -0.0139 -0.0898 0.286 + 11 4.4532 4.6522 3.3149 1.8204 0.0268 0.5054 0.3915 0.0017 0.0000 -0.0158 -0.0928 0.290 + 12 5.1831 4.1429 3.0930 1.6535 0.0108 0.5157 0.3995 -0.0030 0.0000 -0.0187 -0.0968 0.297 + 13 6.0123 3.7903 3.4706 1.4980 0.0016 0.4832 0.3956 -0.0047 0.0000 -0.0200 -0.1060 0.301 + 14 6.9353 3.6075 3.3775 1.3812 0.0035 0.4681 0.3832 -0.0033 0.0000 -0.0203 -0.1036 0.303 + 15 7.8737 3.4215 3.2389 1.2815 0.0040 0.4578 0.3749 -0.0027 0.0000 -0.0204 -0.1017 0.304 + 16 8.8172 3.2345 3.0619 1.1926 0.0043 0.4507 0.3690 -0.0024 0.0000 -0.0202 -0.1003 0.305 + 17 9.7556 3.0486 2.8543 1.1111 0.0048 0.4455 0.3648 -0.0022 0.0000 -0.0201 -0.0992 0.305 + 18 10.6786 2.8657 2.6239 1.0350 0.0055 0.4415 0.3615 -0.0021 0.0000 -0.0200 -0.0984 0.305 + 19 11.5760 2.6879 2.3787 0.9631 0.0064 0.4380 0.3586 -0.0020 0.0000 -0.0197 -0.0975 0.305 + 20 12.4328 2.5181 2.1010 0.8947 0.0075 0.4343 0.3556 -0.0020 0.0000 -0.0194 -0.0966 0.305 + 21 13.2400 2.3582 1.8520 0.8287 0.0091 0.4296 0.3517 -0.0019 0.0000 -0.0190 -0.0953 0.304 + 22 13.9941 2.2087 1.6074 0.7636 0.0113 0.4226 0.3460 -0.0018 0.0000 -0.0183 -0.0934 0.303 + 23 14.6868 2.0715 1.3716 0.6973 0.0142 0.4115 0.3369 -0.0017 0.0000 -0.0172 -0.0904 0.301 + 24 15.3105 1.9479 1.1479 0.6274 0.0179 0.3937 0.3223 -0.0015 0.0000 -0.0155 -0.0857 0.298 + 25 15.8583 1.8393 0.9381 0.5502 0.0222 0.3657 0.2994 -0.0012 0.0000 -0.0137 -0.0790 0.296 + 26 16.3244 1.7470 0.7427 0.4629 0.0266 0.3239 0.2652 -0.0001 0.0000 -0.0133 -0.0710 0.300 + 27 16.6722 1.4928 0.4131 0.3695 0.0316 0.8334 0.2478 -0.0041 0.0000 -0.0123 -0.0352 0.300 + 28 16.9098 1.1466 0.2292 0.2747 0.0392 0.8070 0.2400 -0.0086 0.0000 -0.0019 -0.0294 0.258 + 29 17.0696 0.9138 0.1104 0.1703 0.0456 0.6284 0.1869 -0.0120 0.0000 0.0090 -0.0180 0.202 + 30 17.1499 0.7967 0.0322 0.0578 0.0494 0.2451 0.0729 -0.0083 0.0000 0.0071 -0.0053 0.152 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.18464 Clsurf = 0.03390 - CYsurf = 0.01243 Cmsurf = -0.16065 - CDsurf = 0.00352 Cnsurf = -0.00020 - CDisurf = 0.00352 CDvsurf = 0.00000 + CLsurf = 0.18525 Clsurf = 0.03396 + CYsurf = 0.01236 Cmsurf = -0.16098 + CDsurf = 0.00340 Cnsurf = -0.00019 + CDisurf = 0.00340 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.36121 CDsurf = 0.00687 + CLsurf = 0.36240 CDsurf = 0.00663 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 2.6323 0.0858 0.4297 0.3329 0.1974 0.0000 -0.0189 0.0848 0.307 - 32 -0.1025 7.6885 1.0492 2.4987 0.0851 0.4180 0.3238 0.0400 0.0000 -0.0190 0.0819 0.309 - 33 -0.2837 7.5620 1.7073 2.4844 0.0836 0.4230 0.3277 0.0300 0.0000 -0.0177 0.0816 0.304 - 34 -0.5530 7.3741 2.3052 2.4699 0.0809 0.4315 0.3342 0.0266 0.0000 -0.0159 0.0814 0.298 - 35 -0.9075 7.1267 2.8223 2.4431 0.0769 0.4418 0.3422 0.0232 0.0000 -0.0139 0.0814 0.291 - 36 -1.3432 6.8226 3.2414 2.3977 0.0717 0.4530 0.3509 0.0207 0.0000 -0.0122 0.0818 0.285 - 37 -1.8554 6.4651 3.5491 2.3313 0.0658 0.4650 0.3602 0.0179 0.0000 -0.0110 0.0827 0.281 - 38 -2.4386 6.0582 3.7368 2.2322 0.0587 0.4754 0.3682 0.0126 0.0000 -0.0107 0.0840 0.279 - 39 -3.0862 5.6062 3.8005 2.1085 0.0485 0.4854 0.3760 0.0094 0.0000 -0.0113 0.0861 0.280 - 40 -3.7613 5.1351 3.4440 1.9663 0.0378 0.4944 0.3829 0.0057 0.0000 -0.0130 0.0888 0.284 - 41 -4.4532 4.6522 3.3149 1.8135 0.0268 0.5035 0.3900 0.0018 0.0000 -0.0159 0.0926 0.291 - 42 -5.1831 4.1429 3.0930 1.6504 0.0115 0.5148 0.3987 -0.0029 0.0000 -0.0197 0.0975 0.299 - 43 -6.0123 3.7903 3.4706 1.4952 0.0021 0.4823 0.3949 -0.0047 0.0000 -0.0215 0.1072 0.305 - 44 -6.9353 3.6075 3.3775 1.3789 0.0037 0.4673 0.3826 -0.0033 0.0000 -0.0220 0.1049 0.308 - 45 -7.8737 3.4215 3.2389 1.2796 0.0041 0.4572 0.3743 -0.0027 0.0000 -0.0221 0.1031 0.309 - 46 -8.8172 3.2345 3.0619 1.1910 0.0044 0.4501 0.3685 -0.0024 0.0000 -0.0220 0.1017 0.310 - 47 -9.7556 3.0486 2.8543 1.1097 0.0049 0.4449 0.3643 -0.0022 0.0000 -0.0219 0.1007 0.310 - 48 -10.6786 2.8657 2.6240 1.0338 0.0056 0.4410 0.3610 -0.0020 0.0000 -0.0217 0.0998 0.310 - 49 -11.5760 2.6879 2.3787 0.9621 0.0064 0.4375 0.3582 -0.0020 0.0000 -0.0215 0.0990 0.310 - 50 -12.4328 2.5181 2.1010 0.8939 0.0075 0.4339 0.3553 -0.0019 0.0000 -0.0212 0.0981 0.310 - 51 -13.2400 2.3582 1.8520 0.8280 0.0091 0.4292 0.3514 -0.0019 0.0000 -0.0207 0.0968 0.309 - 52 -13.9941 2.2087 1.6074 0.7630 0.0113 0.4223 0.3457 -0.0018 0.0000 -0.0200 0.0949 0.308 - 53 -14.6868 2.0715 1.3716 0.6970 0.0142 0.4113 0.3367 -0.0017 0.0000 -0.0189 0.0919 0.306 - 54 -15.3105 1.9479 1.1479 0.6273 0.0180 0.3936 0.3223 -0.0015 0.0000 -0.0173 0.0873 0.304 - 55 -15.8583 1.8393 0.9381 0.5503 0.0223 0.3657 0.2994 -0.0011 0.0000 -0.0154 0.0805 0.302 - 56 -16.3244 1.7470 0.7427 0.4635 0.0269 0.3242 0.2655 -0.0001 0.0000 -0.0151 0.0726 0.307 - 57 -16.6722 1.4928 0.4131 0.3700 0.0319 0.8345 0.2482 -0.0040 0.0000 -0.0137 0.0359 0.305 - 58 -16.9098 1.1466 0.2292 0.2749 0.0393 0.8076 0.2401 -0.0085 0.0000 -0.0030 0.0300 0.262 - 59 -17.0696 0.9138 0.1104 0.1703 0.0455 0.6285 0.1869 -0.0119 0.0000 0.0083 0.0184 0.206 - 60 -17.1499 0.7967 0.0322 0.0577 0.0486 0.2449 0.0728 -0.0082 0.0000 0.0069 0.0054 0.155 + 31 -0.0114 7.7520 0.3539 2.6499 0.0857 0.4327 0.3351 0.1977 0.0000 -0.0204 0.0865 0.311 + 32 -0.1025 7.6885 1.0491 2.5149 0.0851 0.4207 0.3259 0.0400 0.0000 -0.0203 0.0834 0.312 + 33 -0.2837 7.5620 1.7073 2.5007 0.0839 0.4258 0.3298 0.0300 0.0000 -0.0191 0.0831 0.308 + 34 -0.5530 7.3741 2.3052 2.4857 0.0814 0.4343 0.3364 0.0258 0.0000 -0.0173 0.0830 0.301 + 35 -0.9075 7.1267 2.8223 2.4594 0.0775 0.4447 0.3445 0.0240 0.0000 -0.0153 0.0830 0.294 + 36 -1.3432 6.8226 3.2414 2.4135 0.0723 0.4560 0.3533 0.0201 0.0000 -0.0136 0.0833 0.288 + 37 -1.8554 6.4651 3.5491 2.3435 0.0664 0.4675 0.3622 0.0151 0.0000 -0.0124 0.0841 0.284 + 38 -2.4386 6.0582 3.7368 2.2473 0.0594 0.4786 0.3707 0.0125 0.0000 -0.0118 0.0854 0.282 + 39 -3.0862 5.6062 3.8005 2.1247 0.0495 0.4891 0.3789 0.0091 0.0000 -0.0122 0.0874 0.282 + 40 -3.7613 5.1351 3.4440 1.9706 0.0385 0.4955 0.3838 0.0054 0.0000 -0.0139 0.0898 0.286 + 41 -4.4532 4.6522 3.3149 1.8204 0.0268 0.5054 0.3915 0.0017 0.0000 -0.0158 0.0928 0.290 + 42 -5.1831 4.1429 3.0930 1.6535 0.0108 0.5157 0.3995 -0.0030 0.0000 -0.0187 0.0968 0.297 + 43 -6.0123 3.7903 3.4706 1.4980 0.0016 0.4832 0.3956 -0.0047 0.0000 -0.0200 0.1060 0.301 + 44 -6.9353 3.6075 3.3775 1.3812 0.0035 0.4681 0.3832 -0.0033 0.0000 -0.0203 0.1036 0.303 + 45 -7.8737 3.4215 3.2389 1.2815 0.0040 0.4578 0.3749 -0.0027 0.0000 -0.0204 0.1017 0.304 + 46 -8.8172 3.2345 3.0619 1.1926 0.0043 0.4507 0.3690 -0.0024 0.0000 -0.0202 0.1003 0.305 + 47 -9.7556 3.0486 2.8543 1.1111 0.0048 0.4455 0.3648 -0.0022 0.0000 -0.0201 0.0992 0.305 + 48 -10.6786 2.8657 2.6239 1.0350 0.0055 0.4415 0.3615 -0.0021 0.0000 -0.0200 0.0984 0.305 + 49 -11.5760 2.6879 2.3787 0.9631 0.0064 0.4380 0.3586 -0.0020 0.0000 -0.0197 0.0975 0.305 + 50 -12.4328 2.5181 2.1010 0.8947 0.0075 0.4343 0.3556 -0.0020 0.0000 -0.0194 0.0966 0.305 + 51 -13.2400 2.3582 1.8520 0.8287 0.0091 0.4296 0.3517 -0.0019 0.0000 -0.0190 0.0953 0.304 + 52 -13.9941 2.2087 1.6074 0.7636 0.0113 0.4226 0.3460 -0.0018 0.0000 -0.0183 0.0934 0.303 + 53 -14.6868 2.0715 1.3716 0.6973 0.0142 0.4115 0.3369 -0.0017 0.0000 -0.0172 0.0904 0.301 + 54 -15.3105 1.9479 1.1479 0.6274 0.0179 0.3937 0.3223 -0.0015 0.0000 -0.0155 0.0857 0.298 + 55 -15.8583 1.8393 0.9381 0.5502 0.0222 0.3657 0.2994 -0.0012 0.0000 -0.0137 0.0790 0.296 + 56 -16.3244 1.7470 0.7427 0.4629 0.0266 0.3239 0.2652 -0.0001 0.0000 -0.0133 0.0710 0.300 + 57 -16.6722 1.4928 0.4131 0.3695 0.0316 0.8334 0.2478 -0.0041 0.0000 -0.0123 0.0352 0.300 + 58 -16.9098 1.1466 0.2292 0.2747 0.0392 0.8070 0.2400 -0.0086 0.0000 -0.0019 0.0294 0.258 + 59 -17.0696 0.9138 0.1104 0.1703 0.0456 0.6284 0.1869 -0.0120 0.0000 0.0090 0.0180 0.202 + 60 -17.1499 0.7967 0.0322 0.0578 0.0494 0.2451 0.0729 -0.0083 0.0000 0.0071 0.0053 0.152 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00245 Clsurf = -0.00040 - CYsurf = -0.00038 Cmsurf = -0.01258 - CDsurf = 0.00007 Cnsurf = 0.00024 - CDisurf = 0.00007 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00230 Clsurf = -0.00039 + CYsurf = -0.00036 Cmsurf = -0.01187 + CDsurf = 0.00006 Cnsurf = 0.00023 + CDisurf = 0.00006 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01490 CDsurf = 0.00041 + CLsurf = 0.01399 CDsurf = 0.00038 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.0074 0.0438 -0.0022 -0.0017 -0.0000 0.0000 -0.0010 -0.0005 -0.350 - 62 0.0418 4.2566 0.2392 -0.0075 0.0437 -0.0023 -0.0017 -0.0001 0.0000 -0.0010 -0.0005 -0.349 - 63 0.1156 4.2274 0.3930 -0.0074 0.0435 -0.0023 -0.0017 -0.0001 0.0000 -0.0011 -0.0005 -0.359 - 64 0.2254 4.1839 0.5386 -0.0072 0.0431 -0.0022 -0.0017 -0.0001 0.0000 -0.0011 -0.0005 -0.381 - 65 0.3698 4.1268 0.6730 -0.0069 0.0426 -0.0022 -0.0017 -0.0001 0.0000 -0.0011 -0.0006 -0.421 - 66 0.5474 4.0565 0.7936 -0.0063 0.0418 -0.0020 -0.0015 -0.0001 0.0000 -0.0012 -0.0006 -0.496 - 67 0.7617 3.9717 0.9441 -0.0052 0.0407 -0.0017 -0.0013 -0.0001 0.0000 -0.0012 -0.0007 -0.655 - 68 1.0116 3.8728 1.0344 -0.0035 0.0395 -0.0012 -0.0009 -0.0000 0.0000 -0.0012 -0.0008 - 69 1.2891 3.7630 1.1046 -0.0010 0.0380 -0.0003 -0.0003 -0.0000 0.0000 -0.0013 -0.0010 - 70 1.5912 3.6435 1.1542 0.0027 0.0365 0.0010 0.0007 0.0000 0.0000 -0.0013 -0.0013 - 71 1.9146 3.5155 1.1831 0.0077 0.0350 0.0028 0.0022 0.0001 0.0000 -0.0013 -0.0016 0.850 - 72 2.2558 3.3805 1.1921 0.0141 0.0335 0.0054 0.0042 0.0001 0.0000 -0.0013 -0.0020 0.562 - 73 2.6109 3.2400 1.1821 0.0219 0.0321 0.0088 0.0068 0.0002 0.0000 -0.0013 -0.0025 0.436 - 74 2.9762 3.0955 1.1548 0.0310 0.0308 0.0130 0.0100 0.0003 0.0000 -0.0012 -0.0031 0.368 - 75 3.3476 2.9485 1.1122 0.0409 0.0297 0.0180 0.0139 0.0005 0.0000 -0.0011 -0.0038 0.326 - 76 3.7210 2.8008 1.0564 0.0512 0.0286 0.0237 0.0183 0.0006 0.0000 -0.0009 -0.0047 0.299 - 77 4.0924 2.6538 0.9900 0.0613 0.0278 0.0300 0.0231 0.0007 0.0000 -0.0007 -0.0055 0.281 - 78 4.4577 2.5093 0.9155 0.0707 0.0272 0.0365 0.0282 0.0009 0.0000 -0.0005 -0.0064 0.267 - 79 4.8128 2.3687 0.8353 0.0788 0.0268 0.0431 0.0333 0.0010 0.0000 -0.0002 -0.0073 0.256 - 80 5.1540 2.2338 0.7518 0.0852 0.0266 0.0494 0.0381 0.0011 0.0000 0.0001 -0.0080 0.246 - 81 5.4774 2.1058 0.6671 0.0893 0.0266 0.0550 0.0424 0.0011 0.0000 0.0005 -0.0086 0.237 - 82 5.7795 1.9862 0.5830 0.0911 0.0268 0.0595 0.0459 0.0012 0.0000 0.0010 -0.0089 0.228 - 83 6.0570 1.8764 0.5012 0.0903 0.0271 0.0624 0.0481 0.0012 0.0000 0.0016 -0.0089 0.218 - 84 6.3069 1.7776 0.4225 0.0869 0.0275 0.0634 0.0489 0.0011 0.0000 0.0022 -0.0086 0.206 - 85 6.5264 1.6907 0.3478 0.0809 0.0279 0.0620 0.0478 0.0010 0.0000 0.0028 -0.0078 0.191 - 86 6.7314 1.6096 0.3326 0.0720 0.0284 0.0580 0.0447 0.0009 0.0000 0.0034 -0.0067 0.174 - 87 6.9144 1.5372 0.2507 0.0595 0.0288 0.0502 0.0387 0.0007 0.0000 0.0037 -0.0051 0.153 - 88 7.0535 1.4822 0.1746 0.0445 0.0292 0.0389 0.0300 0.0005 0.0000 0.0035 -0.0034 0.132 - 89 7.1471 1.4451 0.1029 0.0275 0.0294 0.0246 0.0190 0.0003 0.0000 0.0026 -0.0019 0.114 - 90 7.1941 1.4265 0.0340 0.0093 0.0295 0.0084 0.0065 0.0000 0.0000 0.0010 -0.0006 0.103 + 61 0.0047 4.2713 0.0803 -0.0117 0.0439 -0.0036 -0.0028 -0.0000 0.0000 -0.0010 -0.0003 -0.112 + 62 0.0418 4.2566 0.2392 -0.0118 0.0438 -0.0036 -0.0028 -0.0001 0.0000 -0.0010 -0.0003 -0.112 + 63 0.1156 4.2274 0.3930 -0.0118 0.0436 -0.0036 -0.0028 -0.0001 0.0000 -0.0010 -0.0003 -0.119 + 64 0.2254 4.1839 0.5386 -0.0116 0.0432 -0.0036 -0.0028 -0.0001 0.0000 -0.0011 -0.0003 -0.131 + 65 0.3698 4.1268 0.6730 -0.0113 0.0427 -0.0035 -0.0027 -0.0001 0.0000 -0.0011 -0.0003 -0.151 + 66 0.5474 4.0565 0.7936 -0.0106 0.0419 -0.0034 -0.0026 -0.0001 0.0000 -0.0011 -0.0004 -0.184 + 67 0.7617 3.9717 0.9441 -0.0096 0.0408 -0.0031 -0.0024 -0.0001 0.0000 -0.0012 -0.0005 -0.242 + 68 1.0116 3.8728 1.0344 -0.0078 0.0396 -0.0026 -0.0020 -0.0001 0.0000 -0.0012 -0.0006 -0.360 + 69 1.2891 3.7630 1.1046 -0.0052 0.0381 -0.0018 -0.0014 -0.0001 0.0000 -0.0013 -0.0008 -0.678 + 70 1.5912 3.6435 1.1542 -0.0014 0.0366 -0.0005 -0.0004 -0.0000 0.0000 -0.0013 -0.0010 + 71 1.9146 3.5155 1.1831 0.0037 0.0352 0.0014 0.0011 0.0000 0.0000 -0.0013 -0.0013 1.495 + 72 2.2558 3.3805 1.1921 0.0103 0.0337 0.0040 0.0031 0.0001 0.0000 -0.0013 -0.0018 0.680 + 73 2.6109 3.2400 1.1821 0.0184 0.0323 0.0074 0.0057 0.0002 0.0000 -0.0013 -0.0023 0.475 + 74 2.9762 3.0955 1.1548 0.0277 0.0310 0.0116 0.0089 0.0003 0.0000 -0.0012 -0.0029 0.384 + 75 3.3476 2.9485 1.1122 0.0379 0.0298 0.0167 0.0129 0.0004 0.0000 -0.0011 -0.0036 0.334 + 76 3.7210 2.8008 1.0564 0.0485 0.0287 0.0225 0.0173 0.0006 0.0000 -0.0009 -0.0045 0.303 + 77 4.0924 2.6538 0.9900 0.0590 0.0279 0.0288 0.0222 0.0007 0.0000 -0.0007 -0.0053 0.283 + 78 4.4577 2.5093 0.9155 0.0687 0.0273 0.0355 0.0274 0.0008 0.0000 -0.0005 -0.0062 0.268 + 79 4.8128 2.3687 0.8353 0.0771 0.0269 0.0422 0.0325 0.0010 0.0000 -0.0002 -0.0071 0.256 + 80 5.1540 2.2338 0.7518 0.0837 0.0267 0.0486 0.0375 0.0011 0.0000 0.0001 -0.0079 0.247 + 81 5.4774 2.1058 0.6671 0.0881 0.0267 0.0542 0.0418 0.0011 0.0000 0.0005 -0.0085 0.237 + 82 5.7795 1.9862 0.5830 0.0901 0.0268 0.0588 0.0453 0.0012 0.0000 0.0010 -0.0088 0.228 + 83 6.0570 1.8764 0.5012 0.0895 0.0271 0.0618 0.0477 0.0012 0.0000 0.0015 -0.0089 0.218 + 84 6.3069 1.7776 0.4225 0.0862 0.0275 0.0629 0.0485 0.0011 0.0000 0.0022 -0.0085 0.205 + 85 6.5264 1.6907 0.3478 0.0803 0.0279 0.0616 0.0475 0.0010 0.0000 0.0028 -0.0078 0.191 + 86 6.7314 1.6096 0.3326 0.0716 0.0284 0.0577 0.0445 0.0009 0.0000 0.0034 -0.0066 0.174 + 87 6.9144 1.5372 0.2507 0.0592 0.0288 0.0499 0.0385 0.0007 0.0000 0.0037 -0.0051 0.153 + 88 7.0535 1.4822 0.1746 0.0442 0.0292 0.0387 0.0298 0.0005 0.0000 0.0035 -0.0034 0.132 + 89 7.1471 1.4451 0.1029 0.0273 0.0294 0.0245 0.0189 0.0003 0.0000 0.0026 -0.0019 0.114 + 90 7.1941 1.4265 0.0340 0.0092 0.0296 0.0084 0.0065 0.0000 0.0000 0.0010 -0.0006 0.103 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00245 Clsurf = 0.00040 - CYsurf = 0.00038 Cmsurf = -0.01258 - CDsurf = 0.00007 Cnsurf = -0.00024 - CDisurf = 0.00007 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00230 Clsurf = 0.00039 + CYsurf = 0.00036 Cmsurf = -0.01187 + CDsurf = 0.00006 Cnsurf = -0.00023 + CDisurf = 0.00006 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01490 CDsurf = 0.00041 + CLsurf = 0.01399 CDsurf = 0.00038 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.0074 0.0438 -0.0022 -0.0017 -0.0000 0.0000 -0.0010 0.0005 -0.350 - 92 -0.0418 4.2566 0.2392 -0.0075 0.0437 -0.0023 -0.0017 -0.0001 0.0000 -0.0010 0.0005 -0.349 - 93 -0.1156 4.2274 0.3930 -0.0074 0.0435 -0.0023 -0.0017 -0.0001 0.0000 -0.0011 0.0005 -0.359 - 94 -0.2254 4.1839 0.5386 -0.0072 0.0431 -0.0022 -0.0017 -0.0001 0.0000 -0.0011 0.0005 -0.381 - 95 -0.3698 4.1268 0.6730 -0.0069 0.0426 -0.0022 -0.0017 -0.0001 0.0000 -0.0011 0.0006 -0.421 - 96 -0.5474 4.0565 0.7936 -0.0063 0.0418 -0.0020 -0.0015 -0.0001 0.0000 -0.0012 0.0006 -0.496 - 97 -0.7617 3.9717 0.9441 -0.0052 0.0407 -0.0017 -0.0013 -0.0001 0.0000 -0.0012 0.0007 -0.655 - 98 -1.0116 3.8728 1.0344 -0.0035 0.0395 -0.0012 -0.0009 -0.0000 0.0000 -0.0012 0.0008 - 99 -1.2891 3.7630 1.1046 -0.0010 0.0380 -0.0003 -0.0003 -0.0000 0.0000 -0.0013 0.0010 - 100 -1.5912 3.6435 1.1542 0.0027 0.0365 0.0010 0.0007 0.0000 0.0000 -0.0013 0.0013 - 101 -1.9146 3.5155 1.1831 0.0077 0.0350 0.0028 0.0022 0.0001 0.0000 -0.0013 0.0016 0.850 - 102 -2.2558 3.3805 1.1921 0.0141 0.0335 0.0054 0.0042 0.0001 0.0000 -0.0013 0.0020 0.562 - 103 -2.6109 3.2400 1.1821 0.0219 0.0321 0.0088 0.0068 0.0002 0.0000 -0.0013 0.0025 0.436 - 104 -2.9762 3.0955 1.1548 0.0310 0.0308 0.0130 0.0100 0.0003 0.0000 -0.0012 0.0031 0.368 - 105 -3.3476 2.9485 1.1122 0.0409 0.0297 0.0180 0.0139 0.0005 0.0000 -0.0011 0.0038 0.326 - 106 -3.7210 2.8008 1.0564 0.0512 0.0286 0.0237 0.0183 0.0006 0.0000 -0.0009 0.0047 0.299 - 107 -4.0924 2.6538 0.9900 0.0613 0.0278 0.0300 0.0231 0.0007 0.0000 -0.0007 0.0055 0.281 - 108 -4.4577 2.5093 0.9155 0.0707 0.0272 0.0365 0.0282 0.0009 0.0000 -0.0005 0.0064 0.267 - 109 -4.8128 2.3687 0.8353 0.0788 0.0268 0.0431 0.0333 0.0010 0.0000 -0.0002 0.0073 0.256 - 110 -5.1540 2.2338 0.7518 0.0852 0.0266 0.0494 0.0381 0.0011 0.0000 0.0001 0.0080 0.246 - 111 -5.4774 2.1058 0.6671 0.0893 0.0266 0.0550 0.0424 0.0011 0.0000 0.0005 0.0086 0.237 - 112 -5.7795 1.9862 0.5830 0.0911 0.0268 0.0595 0.0459 0.0012 0.0000 0.0010 0.0089 0.228 - 113 -6.0570 1.8764 0.5012 0.0903 0.0271 0.0624 0.0481 0.0012 0.0000 0.0016 0.0089 0.218 - 114 -6.3069 1.7776 0.4225 0.0869 0.0275 0.0634 0.0489 0.0011 0.0000 0.0022 0.0086 0.206 - 115 -6.5264 1.6907 0.3478 0.0809 0.0279 0.0620 0.0478 0.0010 0.0000 0.0028 0.0078 0.191 - 116 -6.7314 1.6096 0.3326 0.0720 0.0284 0.0580 0.0447 0.0009 0.0000 0.0034 0.0067 0.174 - 117 -6.9144 1.5372 0.2507 0.0595 0.0288 0.0502 0.0387 0.0007 0.0000 0.0037 0.0051 0.153 - 118 -7.0535 1.4822 0.1746 0.0444 0.0292 0.0389 0.0300 0.0005 0.0000 0.0035 0.0034 0.132 - 119 -7.1471 1.4451 0.1029 0.0275 0.0294 0.0246 0.0190 0.0003 0.0000 0.0026 0.0019 0.114 - 120 -7.1941 1.4265 0.0340 0.0093 0.0295 0.0084 0.0065 0.0000 0.0000 0.0010 0.0006 0.103 + 91 -0.0047 4.2713 0.0803 -0.0117 0.0439 -0.0036 -0.0028 -0.0000 0.0000 -0.0010 0.0003 -0.112 + 92 -0.0418 4.2566 0.2392 -0.0118 0.0438 -0.0036 -0.0028 -0.0001 0.0000 -0.0010 0.0003 -0.112 + 93 -0.1156 4.2274 0.3930 -0.0118 0.0436 -0.0036 -0.0028 -0.0001 0.0000 -0.0010 0.0003 -0.119 + 94 -0.2254 4.1839 0.5386 -0.0116 0.0432 -0.0036 -0.0028 -0.0001 0.0000 -0.0011 0.0003 -0.131 + 95 -0.3698 4.1268 0.6730 -0.0113 0.0427 -0.0035 -0.0027 -0.0001 0.0000 -0.0011 0.0003 -0.151 + 96 -0.5474 4.0565 0.7936 -0.0106 0.0419 -0.0034 -0.0026 -0.0001 0.0000 -0.0011 0.0004 -0.184 + 97 -0.7617 3.9717 0.9441 -0.0096 0.0408 -0.0031 -0.0024 -0.0001 0.0000 -0.0012 0.0005 -0.242 + 98 -1.0116 3.8728 1.0344 -0.0078 0.0396 -0.0026 -0.0020 -0.0001 0.0000 -0.0012 0.0006 -0.360 + 99 -1.2891 3.7630 1.1046 -0.0052 0.0381 -0.0018 -0.0014 -0.0001 0.0000 -0.0013 0.0008 -0.678 + 100 -1.5912 3.6435 1.1542 -0.0014 0.0366 -0.0005 -0.0004 -0.0000 0.0000 -0.0013 0.0010 + 101 -1.9146 3.5155 1.1831 0.0037 0.0352 0.0014 0.0011 0.0000 0.0000 -0.0013 0.0013 1.495 + 102 -2.2558 3.3805 1.1921 0.0103 0.0337 0.0040 0.0031 0.0001 0.0000 -0.0013 0.0018 0.680 + 103 -2.6109 3.2400 1.1821 0.0184 0.0323 0.0074 0.0057 0.0002 0.0000 -0.0013 0.0023 0.475 + 104 -2.9762 3.0955 1.1548 0.0277 0.0310 0.0116 0.0089 0.0003 0.0000 -0.0012 0.0029 0.384 + 105 -3.3476 2.9485 1.1122 0.0379 0.0298 0.0167 0.0129 0.0004 0.0000 -0.0011 0.0036 0.334 + 106 -3.7210 2.8008 1.0564 0.0485 0.0287 0.0225 0.0173 0.0006 0.0000 -0.0009 0.0045 0.303 + 107 -4.0924 2.6538 0.9900 0.0590 0.0279 0.0288 0.0222 0.0007 0.0000 -0.0007 0.0053 0.283 + 108 -4.4577 2.5093 0.9155 0.0687 0.0273 0.0355 0.0274 0.0008 0.0000 -0.0005 0.0062 0.268 + 109 -4.8128 2.3687 0.8353 0.0771 0.0269 0.0422 0.0325 0.0010 0.0000 -0.0002 0.0071 0.256 + 110 -5.1540 2.2338 0.7518 0.0837 0.0267 0.0486 0.0375 0.0011 0.0000 0.0001 0.0079 0.247 + 111 -5.4774 2.1058 0.6671 0.0881 0.0267 0.0542 0.0418 0.0011 0.0000 0.0005 0.0085 0.237 + 112 -5.7795 1.9862 0.5830 0.0901 0.0268 0.0588 0.0453 0.0012 0.0000 0.0010 0.0088 0.228 + 113 -6.0570 1.8764 0.5012 0.0895 0.0271 0.0618 0.0477 0.0012 0.0000 0.0015 0.0089 0.218 + 114 -6.3069 1.7776 0.4225 0.0862 0.0275 0.0629 0.0485 0.0011 0.0000 0.0022 0.0085 0.205 + 115 -6.5264 1.6907 0.3478 0.0803 0.0279 0.0616 0.0475 0.0010 0.0000 0.0028 0.0078 0.191 + 116 -6.7314 1.6096 0.3326 0.0716 0.0284 0.0577 0.0445 0.0009 0.0000 0.0034 0.0066 0.174 + 117 -6.9144 1.5372 0.2507 0.0592 0.0288 0.0499 0.0385 0.0007 0.0000 0.0037 0.0051 0.153 + 118 -7.0535 1.4822 0.1746 0.0442 0.0292 0.0387 0.0298 0.0005 0.0000 0.0035 0.0034 0.132 + 119 -7.1471 1.4451 0.1029 0.0273 0.0294 0.0245 0.0189 0.0003 0.0000 0.0026 0.0019 0.114 + 120 -7.1941 1.4265 0.0340 0.0092 0.0296 0.0084 0.0065 0.0000 0.0000 0.0010 0.0006 0.103 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.217 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.212 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.215 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.202 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.245 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.244 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.201 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.209 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.215 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.219 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.214 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.200 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.186 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.202 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.191 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.169 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.143 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.122 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.107 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.147 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.130 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.113 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00051 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.01603 + CLsurf = -0.00058 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = 0.01610 CDsurf = -0.00011 Cnsurf = -0.00000 CDisurf = -0.00011 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00052 CDsurf = -0.00011 + CLsurf = -0.00059 CDsurf = -0.00011 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.0252 0.0473 -0.0115 -0.0009 -0.0006 0.0000 0.0019 0.0003 - 152 -1.3090 31.2096 11.6724 -0.0235 0.0556 -0.0029 -0.0007 -0.0002 0.0000 0.0021 0.0006 - 153 -0.9350 34.0626 12.7394 -0.0176 0.0618 -0.0013 -0.0005 -0.0001 0.0000 0.0022 0.0008 - 154 -0.5610 36.1619 13.5246 -0.0118 0.0663 -0.0006 -0.0003 0.0001 0.0000 0.0022 0.0010 - 155 -0.1870 37.5332 14.0374 -0.0083 0.0689 -0.0003 -0.0002 0.0002 0.0000 0.0021 0.0015 - 156 0.1870 37.5332 14.0374 -0.0083 0.0689 -0.0003 -0.0002 0.0002 0.0000 0.0021 0.0015 - 157 0.5610 36.1619 13.5246 -0.0118 0.0663 -0.0006 -0.0003 0.0001 0.0000 0.0022 0.0010 - 158 0.9350 34.0626 12.7394 -0.0176 0.0618 -0.0013 -0.0005 -0.0001 0.0000 0.0022 0.0008 - 159 1.3090 31.2096 11.6724 -0.0235 0.0556 -0.0029 -0.0007 -0.0002 0.0000 0.0021 0.0006 - 160 1.6830 26.5957 9.9468 -0.0252 0.0473 -0.0115 -0.0009 -0.0006 0.0000 0.0019 0.0003 + 151 -1.6830 26.5957 9.9468 -0.0270 0.0473 -0.0124 -0.0010 -0.0006 0.0000 0.0019 0.0003 + 152 -1.3090 31.2096 11.6724 -0.0259 0.0556 -0.0032 -0.0008 -0.0002 0.0000 0.0021 0.0006 + 153 -0.9350 34.0626 12.7394 -0.0201 0.0620 -0.0014 -0.0006 -0.0001 0.0000 0.0022 0.0008 + 154 -0.5610 36.1619 13.5246 -0.0143 0.0665 -0.0007 -0.0004 0.0001 0.0000 0.0022 0.0010 + 155 -0.1870 37.5332 14.0374 -0.0108 0.0691 -0.0003 -0.0003 0.0002 0.0000 0.0021 0.0015 + 156 0.1870 37.5332 14.0374 -0.0108 0.0691 -0.0003 -0.0003 0.0002 0.0000 0.0021 0.0015 + 157 0.5610 36.1619 13.5246 -0.0143 0.0665 -0.0007 -0.0004 0.0001 0.0000 0.0022 0.0010 + 158 0.9350 34.0626 12.7394 -0.0201 0.0620 -0.0014 -0.0006 -0.0001 0.0000 0.0022 0.0008 + 159 1.3090 31.2096 11.6724 -0.0259 0.0556 -0.0032 -0.0008 -0.0002 0.0000 0.0021 0.0006 + 160 1.6830 26.5957 9.9468 -0.0270 0.0473 -0.0124 -0.0010 -0.0006 0.0000 0.0019 0.0003 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.491 - 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.473 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.476 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.481 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.528 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.535 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.548 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.553 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.593 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.303 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.428 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.478 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.493 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.480 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.534 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.559 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.561 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.569 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.596 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_04_04.txt b/regression/scripts/AVL/avl_files/strip_forces_case_04_04.txt index 2b836be480..1b24ac6910 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_04_04.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_04_04.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.31531 Clsurf = -0.06091 - CYsurf = -0.01913 Cmsurf = -0.28282 - CDsurf = 0.00907 Cnsurf = -0.00332 - CDisurf = 0.00907 CDvsurf = 0.00000 + CLsurf = 0.31587 Clsurf = -0.06096 + CYsurf = -0.01893 Cmsurf = -0.28311 + CDsurf = 0.00873 Cnsurf = -0.00335 + CDisurf = 0.00873 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.61658 CDsurf = 0.01770 + CLsurf = 0.61763 CDsurf = 0.01705 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 4.1339 0.1404 0.6401 0.4955 0.4543 0.0000 -0.0296 -0.1335 0.310 - 2 0.1025 7.6885 1.0492 3.8232 0.1399 0.6348 0.4914 0.0884 0.0000 -0.0296 -0.1262 0.310 - 3 0.2837 7.5620 1.7073 3.7952 0.1385 0.6434 0.4981 0.0654 0.0000 -0.0277 -0.1256 0.306 - 4 0.5530 7.3741 2.3052 3.7765 0.1357 0.6574 0.5090 0.0585 0.0000 -0.0247 -0.1253 0.299 - 5 0.9075 7.1267 2.8223 3.7451 0.1306 0.6756 0.5230 0.0516 0.0000 -0.0215 -0.1254 0.291 - 6 1.3432 6.8226 3.2414 3.6925 0.1209 0.6965 0.5392 0.0469 0.0000 -0.0185 -0.1262 0.284 - 7 1.8554 6.4651 3.5491 3.6179 0.1034 0.7209 0.5581 0.0417 0.0000 -0.0161 -0.1280 0.279 - 8 2.4386 6.0582 3.7368 3.4983 0.0853 0.7452 0.5769 0.0311 0.0000 -0.0150 -0.1308 0.276 - 9 3.0862 5.6062 3.8005 3.3523 0.0731 0.7725 0.5981 0.0251 0.0000 -0.0149 -0.1349 0.275 - 10 3.7613 5.1351 3.4440 3.1814 0.0618 0.8013 0.6203 0.0180 0.0000 -0.0161 -0.1403 0.276 - 11 4.4532 4.6522 3.3149 2.9953 0.0489 0.8338 0.6455 0.0097 0.0000 -0.0186 -0.1474 0.279 - 12 5.1831 4.1429 3.0930 2.7949 0.0298 0.8749 0.6772 -0.0003 0.0000 -0.0216 -0.1561 0.282 - 13 6.0123 3.7903 3.4706 2.5905 0.0172 0.8413 0.6865 -0.0050 0.0000 -0.0210 -0.1724 0.281 - 14 6.9353 3.6075 3.3775 2.4336 0.0168 0.8302 0.6774 -0.0029 0.0000 -0.0212 -0.1706 0.281 - 15 7.8737 3.4215 3.2389 2.2933 0.0148 0.8248 0.6730 -0.0024 0.0000 -0.0211 -0.1695 0.281 - 16 8.8172 3.2345 3.0619 2.1624 0.0135 0.8227 0.6713 -0.0025 0.0000 -0.0209 -0.1689 0.281 - 17 9.7556 3.0486 2.8543 2.0363 0.0134 0.8220 0.6707 -0.0027 0.0000 -0.0207 -0.1686 0.281 - 18 10.6786 2.8657 2.6240 1.9142 0.0143 0.8220 0.6708 -0.0030 0.0000 -0.0204 -0.1684 0.280 - 19 11.5760 2.6879 2.3787 1.7947 0.0157 0.8217 0.6705 -0.0033 0.0000 -0.0200 -0.1680 0.280 - 20 12.4328 2.5181 2.1010 1.6776 0.0178 0.8199 0.6691 -0.0036 0.0000 -0.0194 -0.1671 0.279 - 21 13.2400 2.3582 1.8520 1.5615 0.0208 0.8150 0.6650 -0.0038 0.0000 -0.0186 -0.1655 0.278 - 22 13.9941 2.2087 1.6074 1.4443 0.0248 0.8048 0.6568 -0.0040 0.0000 -0.0172 -0.1624 0.276 - 23 14.6868 2.0715 1.3716 1.3226 0.0304 0.7859 0.6413 -0.0039 0.0000 -0.0151 -0.1571 0.274 - 24 15.3105 1.9479 1.1479 1.1918 0.0373 0.7531 0.6145 -0.0036 0.0000 -0.0120 -0.1484 0.270 - 25 15.8583 1.8393 0.9381 1.0455 0.0451 0.6995 0.5708 -0.0026 0.0000 -0.0089 -0.1358 0.266 - 26 16.3244 1.7470 0.7427 0.8791 0.0531 0.6189 0.5050 0.0012 0.0000 -0.0099 -0.1220 0.270 - 27 16.6722 1.4928 0.4131 0.6998 0.0617 1.5876 0.4719 -0.0152 0.0000 -0.0109 -0.0625 0.273 - 28 16.9098 1.1466 0.2292 0.5178 0.0734 1.5345 0.4562 -0.0325 0.0000 0.0085 -0.0515 0.231 - 29 17.0696 0.9138 0.1104 0.3195 0.0828 1.1943 0.3550 -0.0459 0.0000 0.0269 -0.0305 0.174 - 30 17.1499 0.7967 0.0322 0.1081 0.0875 0.4682 0.1392 -0.0336 0.0000 0.0180 -0.0084 0.121 + 1 0.0114 7.7520 0.3539 4.1523 0.1403 0.6431 0.4978 0.4550 0.0000 -0.0312 -0.1353 0.313 + 2 0.1025 7.6885 1.0491 3.8394 0.1399 0.6375 0.4935 0.0885 0.0000 -0.0309 -0.1277 0.313 + 3 0.2837 7.5620 1.7073 3.8115 0.1388 0.6461 0.5002 0.0656 0.0000 -0.0291 -0.1271 0.308 + 4 0.5530 7.3741 2.3052 3.7914 0.1362 0.6603 0.5112 0.0565 0.0000 -0.0261 -0.1268 0.301 + 5 0.9075 7.1267 2.8223 3.7610 0.1312 0.6783 0.5251 0.0531 0.0000 -0.0228 -0.1269 0.293 + 6 1.3432 6.8226 3.2414 3.7074 0.1215 0.6995 0.5415 0.0453 0.0000 -0.0199 -0.1278 0.287 + 7 1.8554 6.4651 3.5491 3.6253 0.1040 0.7231 0.5598 0.0351 0.0000 -0.0176 -0.1294 0.281 + 8 2.4386 6.0582 3.7368 3.5134 0.0860 0.7485 0.5795 0.0305 0.0000 -0.0161 -0.1322 0.278 + 9 3.0862 5.6062 3.8005 3.3718 0.0741 0.7771 0.6016 0.0242 0.0000 -0.0156 -0.1362 0.276 + 10 3.7613 5.1351 3.4440 3.1752 0.0625 0.7999 0.6192 0.0170 0.0000 -0.0175 -0.1413 0.278 + 11 4.4532 4.6522 3.3149 3.0005 0.0489 0.8353 0.6466 0.0092 0.0000 -0.0185 -0.1475 0.279 + 12 5.1831 4.1429 3.0930 2.7961 0.0291 0.8753 0.6776 -0.0008 0.0000 -0.0205 -0.1553 0.280 + 13 6.0123 3.7903 3.4706 2.5934 0.0167 0.8422 0.6873 -0.0049 0.0000 -0.0194 -0.1712 0.278 + 14 6.9353 3.6075 3.3775 2.4359 0.0165 0.8310 0.6781 -0.0029 0.0000 -0.0195 -0.1693 0.279 + 15 7.8737 3.4215 3.2389 2.2950 0.0146 0.8254 0.6735 -0.0025 0.0000 -0.0194 -0.1681 0.279 + 16 8.8172 3.2345 3.0619 2.1639 0.0134 0.8233 0.6718 -0.0025 0.0000 -0.0192 -0.1675 0.279 + 17 9.7556 3.0486 2.8543 2.0377 0.0133 0.8225 0.6712 -0.0028 0.0000 -0.0189 -0.1672 0.278 + 18 10.6786 2.8657 2.6239 1.9153 0.0142 0.8225 0.6712 -0.0030 0.0000 -0.0186 -0.1669 0.278 + 19 11.5760 2.6879 2.3787 1.7957 0.0157 0.8222 0.6709 -0.0033 0.0000 -0.0183 -0.1665 0.277 + 20 12.4328 2.5181 2.1010 1.6784 0.0178 0.8203 0.6694 -0.0037 0.0000 -0.0177 -0.1657 0.276 + 21 13.2400 2.3582 1.8520 1.5622 0.0207 0.8154 0.6653 -0.0039 0.0000 -0.0168 -0.1640 0.275 + 22 13.9941 2.2087 1.6074 1.4448 0.0248 0.8051 0.6570 -0.0040 0.0000 -0.0155 -0.1609 0.274 + 23 14.6868 2.0715 1.3716 1.3230 0.0304 0.7861 0.6415 -0.0040 0.0000 -0.0133 -0.1555 0.271 + 24 15.3105 1.9479 1.1479 1.1919 0.0373 0.7531 0.6146 -0.0037 0.0000 -0.0103 -0.1468 0.267 + 25 15.8583 1.8393 0.9381 1.0454 0.0450 0.6995 0.5708 -0.0027 0.0000 -0.0072 -0.1343 0.263 + 26 16.3244 1.7470 0.7427 0.8786 0.0528 0.6186 0.5047 0.0012 0.0000 -0.0082 -0.1204 0.266 + 27 16.6722 1.4928 0.4131 0.6993 0.0613 1.5865 0.4716 -0.0154 0.0000 -0.0095 -0.0618 0.270 + 28 16.9098 1.1466 0.2292 0.5176 0.0734 1.5339 0.4560 -0.0327 0.0000 0.0096 -0.0509 0.229 + 29 17.0696 0.9138 0.1104 0.3195 0.0829 1.1943 0.3550 -0.0461 0.0000 0.0276 -0.0302 0.172 + 30 17.1499 0.7967 0.0322 0.1082 0.0883 0.4685 0.1393 -0.0339 0.0000 0.0181 -0.0083 0.120 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.31531 Clsurf = 0.06091 - CYsurf = 0.01913 Cmsurf = -0.28282 - CDsurf = 0.00907 Cnsurf = 0.00332 - CDisurf = 0.00907 CDvsurf = 0.00000 + CLsurf = 0.31587 Clsurf = 0.06096 + CYsurf = 0.01893 Cmsurf = -0.28311 + CDsurf = 0.00873 Cnsurf = 0.00335 + CDisurf = 0.00873 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.61657 CDsurf = 0.01770 + CLsurf = 0.61763 CDsurf = 0.01705 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 4.1339 0.1405 0.6401 0.4955 0.4543 0.0000 -0.0296 0.1335 0.310 - 32 -0.1025 7.6885 1.0492 3.8232 0.1399 0.6348 0.4914 0.0884 0.0000 -0.0296 0.1262 0.310 - 33 -0.2837 7.5620 1.7073 3.7952 0.1385 0.6434 0.4981 0.0654 0.0000 -0.0277 0.1256 0.306 - 34 -0.5530 7.3741 2.3052 3.7765 0.1357 0.6574 0.5090 0.0585 0.0000 -0.0247 0.1253 0.299 - 35 -0.9075 7.1267 2.8223 3.7451 0.1306 0.6756 0.5230 0.0516 0.0000 -0.0215 0.1254 0.291 - 36 -1.3432 6.8226 3.2414 3.6925 0.1209 0.6965 0.5392 0.0469 0.0000 -0.0185 0.1262 0.284 - 37 -1.8554 6.4651 3.5491 3.6179 0.1034 0.7209 0.5581 0.0417 0.0000 -0.0161 0.1280 0.279 - 38 -2.4386 6.0582 3.7368 3.4983 0.0853 0.7452 0.5769 0.0311 0.0000 -0.0150 0.1308 0.276 - 39 -3.0862 5.6062 3.8005 3.3523 0.0731 0.7725 0.5980 0.0251 0.0000 -0.0149 0.1349 0.275 - 40 -3.7613 5.1351 3.4440 3.1814 0.0618 0.8013 0.6203 0.0180 0.0000 -0.0161 0.1403 0.276 - 41 -4.4532 4.6522 3.3149 2.9953 0.0489 0.8338 0.6455 0.0097 0.0000 -0.0186 0.1474 0.279 - 42 -5.1831 4.1429 3.0930 2.7949 0.0298 0.8748 0.6772 -0.0003 0.0000 -0.0216 0.1561 0.282 - 43 -6.0123 3.7903 3.4706 2.5905 0.0172 0.8413 0.6865 -0.0050 0.0000 -0.0210 0.1724 0.281 - 44 -6.9353 3.6075 3.3775 2.4336 0.0168 0.8302 0.6774 -0.0029 0.0000 -0.0212 0.1706 0.281 - 45 -7.8737 3.4215 3.2389 2.2933 0.0148 0.8248 0.6730 -0.0024 0.0000 -0.0211 0.1695 0.281 - 46 -8.8172 3.2345 3.0619 2.1624 0.0135 0.8227 0.6713 -0.0025 0.0000 -0.0209 0.1689 0.281 - 47 -9.7556 3.0486 2.8543 2.0363 0.0134 0.8220 0.6707 -0.0027 0.0000 -0.0207 0.1686 0.281 - 48 -10.6786 2.8657 2.6240 1.9142 0.0143 0.8220 0.6708 -0.0030 0.0000 -0.0204 0.1684 0.280 - 49 -11.5760 2.6879 2.3787 1.7947 0.0157 0.8217 0.6705 -0.0033 0.0000 -0.0200 0.1680 0.280 - 50 -12.4328 2.5181 2.1010 1.6775 0.0178 0.8199 0.6690 -0.0036 0.0000 -0.0194 0.1671 0.279 - 51 -13.2400 2.3582 1.8520 1.5615 0.0208 0.8150 0.6650 -0.0038 0.0000 -0.0186 0.1655 0.278 - 52 -13.9941 2.2087 1.6074 1.4443 0.0248 0.8048 0.6567 -0.0040 0.0000 -0.0172 0.1624 0.276 - 53 -14.6868 2.0715 1.3716 1.3226 0.0304 0.7859 0.6413 -0.0039 0.0000 -0.0151 0.1571 0.274 - 54 -15.3105 1.9479 1.1479 1.1918 0.0373 0.7531 0.6145 -0.0036 0.0000 -0.0120 0.1484 0.270 - 55 -15.8583 1.8393 0.9381 1.0455 0.0451 0.6995 0.5708 -0.0026 0.0000 -0.0089 0.1358 0.266 - 56 -16.3244 1.7470 0.7427 0.8791 0.0531 0.6189 0.5050 0.0012 0.0000 -0.0099 0.1220 0.270 - 57 -16.6722 1.4928 0.4131 0.6998 0.0617 1.5876 0.4719 -0.0152 0.0000 -0.0109 0.0625 0.273 - 58 -16.9098 1.1466 0.2292 0.5178 0.0734 1.5344 0.4561 -0.0325 0.0000 0.0085 0.0515 0.231 - 59 -17.0696 0.9138 0.1104 0.3195 0.0828 1.1943 0.3550 -0.0459 0.0000 0.0269 0.0305 0.174 - 60 -17.1499 0.7967 0.0322 0.1081 0.0875 0.4682 0.1392 -0.0336 0.0000 0.0180 0.0084 0.121 + 31 -0.0114 7.7520 0.3539 4.1523 0.1403 0.6431 0.4978 0.4550 0.0000 -0.0312 0.1353 0.313 + 32 -0.1025 7.6885 1.0491 3.8394 0.1399 0.6375 0.4935 0.0885 0.0000 -0.0309 0.1277 0.313 + 33 -0.2837 7.5620 1.7073 3.8115 0.1388 0.6461 0.5002 0.0656 0.0000 -0.0291 0.1271 0.308 + 34 -0.5530 7.3741 2.3052 3.7913 0.1362 0.6603 0.5112 0.0565 0.0000 -0.0261 0.1268 0.301 + 35 -0.9075 7.1267 2.8223 3.7610 0.1312 0.6783 0.5251 0.0531 0.0000 -0.0228 0.1269 0.293 + 36 -1.3432 6.8226 3.2414 3.7074 0.1215 0.6995 0.5415 0.0453 0.0000 -0.0199 0.1278 0.287 + 37 -1.8554 6.4651 3.5491 3.6253 0.1040 0.7231 0.5598 0.0351 0.0000 -0.0176 0.1294 0.281 + 38 -2.4386 6.0582 3.7368 3.5134 0.0860 0.7485 0.5795 0.0305 0.0000 -0.0161 0.1322 0.278 + 39 -3.0862 5.6062 3.8005 3.3718 0.0741 0.7771 0.6016 0.0242 0.0000 -0.0156 0.1362 0.276 + 40 -3.7613 5.1351 3.4440 3.1752 0.0625 0.7999 0.6192 0.0170 0.0000 -0.0175 0.1413 0.278 + 41 -4.4532 4.6522 3.3149 3.0005 0.0489 0.8353 0.6466 0.0092 0.0000 -0.0185 0.1475 0.279 + 42 -5.1831 4.1429 3.0930 2.7961 0.0291 0.8753 0.6776 -0.0008 0.0000 -0.0205 0.1553 0.280 + 43 -6.0123 3.7903 3.4706 2.5934 0.0167 0.8422 0.6873 -0.0049 0.0000 -0.0194 0.1712 0.278 + 44 -6.9353 3.6075 3.3775 2.4359 0.0165 0.8310 0.6781 -0.0029 0.0000 -0.0195 0.1693 0.279 + 45 -7.8737 3.4215 3.2389 2.2950 0.0146 0.8254 0.6735 -0.0025 0.0000 -0.0194 0.1681 0.279 + 46 -8.8172 3.2345 3.0619 2.1639 0.0134 0.8233 0.6718 -0.0025 0.0000 -0.0192 0.1675 0.279 + 47 -9.7556 3.0486 2.8543 2.0377 0.0133 0.8225 0.6712 -0.0028 0.0000 -0.0189 0.1672 0.278 + 48 -10.6786 2.8657 2.6239 1.9153 0.0142 0.8225 0.6712 -0.0030 0.0000 -0.0186 0.1669 0.278 + 49 -11.5760 2.6879 2.3787 1.7957 0.0157 0.8222 0.6709 -0.0033 0.0000 -0.0183 0.1665 0.277 + 50 -12.4328 2.5181 2.1010 1.6784 0.0178 0.8203 0.6694 -0.0037 0.0000 -0.0177 0.1657 0.276 + 51 -13.2400 2.3582 1.8520 1.5622 0.0207 0.8154 0.6653 -0.0039 0.0000 -0.0168 0.1640 0.275 + 52 -13.9941 2.2087 1.6074 1.4448 0.0248 0.8051 0.6570 -0.0040 0.0000 -0.0155 0.1609 0.274 + 53 -14.6868 2.0715 1.3716 1.3230 0.0304 0.7861 0.6415 -0.0040 0.0000 -0.0133 0.1555 0.271 + 54 -15.3105 1.9479 1.1479 1.1919 0.0373 0.7531 0.6146 -0.0037 0.0000 -0.0103 0.1468 0.267 + 55 -15.8583 1.8393 0.9381 1.0454 0.0450 0.6995 0.5708 -0.0027 0.0000 -0.0072 0.1343 0.263 + 56 -16.3244 1.7470 0.7427 0.8786 0.0528 0.6186 0.5047 0.0012 0.0000 -0.0082 0.1204 0.266 + 57 -16.6722 1.4928 0.4131 0.6993 0.0613 1.5865 0.4716 -0.0154 0.0000 -0.0095 0.0618 0.270 + 58 -16.9098 1.1466 0.2292 0.5176 0.0734 1.5339 0.4560 -0.0327 0.0000 0.0096 0.0509 0.229 + 59 -17.0696 0.9138 0.1104 0.3195 0.0829 1.1943 0.3550 -0.0461 0.0000 0.0276 0.0302 0.172 + 60 -17.1499 0.7967 0.0322 0.1082 0.0883 0.4685 0.1393 -0.0339 0.0000 0.0181 0.0083 0.120 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02660 Clsurf = -0.00285 - CYsurf = -0.00425 Cmsurf = -0.13013 - CDsurf = 0.00157 Cnsurf = 0.00242 - CDisurf = 0.00157 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02645 Clsurf = -0.00284 + CYsurf = -0.00422 Cmsurf = -0.12942 + CDsurf = 0.00156 Cnsurf = 0.00241 + CDisurf = 0.00156 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16213 CDsurf = 0.00944 + CLsurf = 0.16122 CDsurf = 0.00941 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.5643 0.0924 0.1684 0.1290 0.0418 0.0000 -0.0082 -0.0354 0.314 - 62 0.0418 4.2566 0.2392 0.5172 0.0926 0.1579 0.1210 0.0116 0.0000 -0.0080 -0.0330 0.316 - 63 0.1156 4.2274 0.3930 0.5139 0.0926 0.1582 0.1212 0.0097 0.0000 -0.0076 -0.0327 0.313 - 64 0.2254 4.1839 0.5386 0.5131 0.0921 0.1596 0.1223 0.0093 0.0000 -0.0070 -0.0324 0.307 - 65 0.3698 4.1268 0.6730 0.5130 0.0912 0.1619 0.1240 0.0092 0.0000 -0.0062 -0.0321 0.300 - 66 0.5474 4.0565 0.7936 0.5130 0.0896 0.1647 0.1261 0.0091 0.0000 -0.0054 -0.0319 0.293 - 67 0.7617 3.9717 0.9441 0.5125 0.0873 0.1681 0.1287 0.0091 0.0000 -0.0046 -0.0318 0.286 - 68 1.0116 3.8728 1.0344 0.5120 0.0841 0.1722 0.1319 0.0091 0.0000 -0.0039 -0.0318 0.279 - 69 1.2891 3.7630 1.1046 0.5112 0.0801 0.1770 0.1355 0.0092 0.0000 -0.0032 -0.0321 0.274 - 70 1.5912 3.6435 1.1542 0.5103 0.0757 0.1825 0.1398 0.0092 0.0000 -0.0027 -0.0325 0.269 - 71 1.9146 3.5155 1.1831 0.5094 0.0713 0.1888 0.1446 0.0094 0.0000 -0.0022 -0.0332 0.265 - 72 2.2558 3.3805 1.1921 0.5085 0.0673 0.1960 0.1501 0.0095 0.0000 -0.0018 -0.0341 0.262 - 73 2.6109 3.2400 1.1821 0.5076 0.0641 0.2042 0.1564 0.0097 0.0000 -0.0015 -0.0351 0.259 - 74 2.9762 3.0955 1.1548 0.5067 0.0615 0.2134 0.1634 0.0099 0.0000 -0.0011 -0.0363 0.257 - 75 3.3476 2.9485 1.1122 0.5052 0.0596 0.2234 0.1711 0.0100 0.0000 -0.0007 -0.0376 0.254 - 76 3.7210 2.8008 1.0564 0.5027 0.0583 0.2341 0.1793 0.0101 0.0000 -0.0002 -0.0390 0.251 - 77 4.0924 2.6538 0.9900 0.4985 0.0574 0.2450 0.1877 0.0102 0.0000 0.0003 -0.0404 0.249 - 78 4.4577 2.5093 0.9155 0.4921 0.0569 0.2558 0.1960 0.0103 0.0000 0.0009 -0.0417 0.246 - 79 4.8128 2.3687 0.8353 0.4826 0.0569 0.2658 0.2036 0.0102 0.0000 0.0016 -0.0427 0.242 - 80 5.1540 2.2338 0.7518 0.4696 0.0574 0.2744 0.2101 0.0101 0.0000 0.0025 -0.0433 0.238 - 81 5.4774 2.1058 0.6671 0.4526 0.0583 0.2805 0.2149 0.0099 0.0000 0.0037 -0.0434 0.233 - 82 5.7795 1.9862 0.5830 0.4307 0.0596 0.2831 0.2168 0.0094 0.0000 0.0051 -0.0426 0.226 - 83 6.0570 1.8764 0.5012 0.4040 0.0612 0.2811 0.2153 0.0089 0.0000 0.0069 -0.0408 0.218 - 84 6.3069 1.7776 0.4225 0.3717 0.0631 0.2731 0.2092 0.0081 0.0000 0.0089 -0.0378 0.208 - 85 6.5264 1.6907 0.3478 0.3341 0.0650 0.2582 0.1978 0.0072 0.0000 0.0109 -0.0336 0.195 - 86 6.7314 1.6096 0.3326 0.2890 0.0670 0.2346 0.1797 0.0060 0.0000 0.0128 -0.0281 0.179 - 87 6.9144 1.5372 0.2507 0.2334 0.0688 0.1985 0.1520 0.0045 0.0000 0.0138 -0.0213 0.159 - 88 7.0535 1.4822 0.1746 0.1715 0.0702 0.1513 0.1159 0.0028 0.0000 0.0129 -0.0142 0.139 - 89 7.1471 1.4451 0.1029 0.1049 0.0712 0.0950 0.0727 0.0012 0.0000 0.0094 -0.0078 0.121 - 90 7.1941 1.4265 0.0340 0.0353 0.0718 0.0325 0.0249 -0.0004 0.0000 0.0035 -0.0025 0.111 + 61 0.0047 4.2713 0.0803 0.5590 0.0925 0.1668 0.1278 0.0412 0.0000 -0.0082 -0.0351 0.314 + 62 0.0418 4.2566 0.2392 0.5127 0.0927 0.1565 0.1199 0.0115 0.0000 -0.0080 -0.0327 0.316 + 63 0.1156 4.2274 0.3930 0.5095 0.0926 0.1568 0.1201 0.0096 0.0000 -0.0076 -0.0324 0.313 + 64 0.2254 4.1839 0.5386 0.5086 0.0922 0.1583 0.1212 0.0092 0.0000 -0.0070 -0.0321 0.308 + 65 0.3698 4.1268 0.6730 0.5087 0.0913 0.1605 0.1229 0.0091 0.0000 -0.0062 -0.0319 0.301 + 66 0.5474 4.0565 0.7936 0.5085 0.0897 0.1632 0.1250 0.0091 0.0000 -0.0054 -0.0316 0.293 + 67 0.7617 3.9717 0.9441 0.5083 0.0874 0.1667 0.1277 0.0090 0.0000 -0.0046 -0.0315 0.286 + 68 1.0116 3.8728 1.0344 0.5076 0.0842 0.1707 0.1308 0.0090 0.0000 -0.0039 -0.0316 0.280 + 69 1.2891 3.7630 1.1046 0.5070 0.0802 0.1755 0.1344 0.0091 0.0000 -0.0032 -0.0318 0.274 + 70 1.5912 3.6435 1.1542 0.5062 0.0758 0.1810 0.1387 0.0092 0.0000 -0.0027 -0.0323 0.269 + 71 1.9146 3.5155 1.1831 0.5054 0.0714 0.1873 0.1435 0.0093 0.0000 -0.0022 -0.0330 0.266 + 72 2.2558 3.3805 1.1921 0.5047 0.0675 0.1946 0.1490 0.0094 0.0000 -0.0018 -0.0338 0.262 + 73 2.6109 3.2400 1.1821 0.5042 0.0642 0.2029 0.1554 0.0096 0.0000 -0.0015 -0.0349 0.260 + 74 2.9762 3.0955 1.1548 0.5035 0.0617 0.2121 0.1624 0.0098 0.0000 -0.0011 -0.0361 0.257 + 75 3.3476 2.9485 1.1122 0.5023 0.0598 0.2221 0.1701 0.0100 0.0000 -0.0007 -0.0374 0.254 + 76 3.7210 2.8008 1.0564 0.5000 0.0584 0.2328 0.1783 0.0101 0.0000 -0.0003 -0.0388 0.252 + 77 4.0924 2.6538 0.9900 0.4962 0.0575 0.2439 0.1868 0.0102 0.0000 0.0002 -0.0402 0.249 + 78 4.4577 2.5093 0.9155 0.4901 0.0570 0.2548 0.1951 0.0102 0.0000 0.0009 -0.0415 0.246 + 79 4.8128 2.3687 0.8353 0.4809 0.0570 0.2649 0.2029 0.0102 0.0000 0.0016 -0.0425 0.242 + 80 5.1540 2.2338 0.7518 0.4682 0.0574 0.2735 0.2095 0.0101 0.0000 0.0025 -0.0432 0.238 + 81 5.4774 2.1058 0.6671 0.4513 0.0583 0.2797 0.2143 0.0099 0.0000 0.0037 -0.0433 0.233 + 82 5.7795 1.9862 0.5830 0.4297 0.0596 0.2824 0.2163 0.0094 0.0000 0.0051 -0.0425 0.226 + 83 6.0570 1.8764 0.5012 0.4031 0.0613 0.2805 0.2149 0.0089 0.0000 0.0069 -0.0407 0.218 + 84 6.3069 1.7776 0.4225 0.3711 0.0632 0.2727 0.2089 0.0081 0.0000 0.0089 -0.0377 0.208 + 85 6.5264 1.6907 0.3478 0.3337 0.0651 0.2578 0.1975 0.0072 0.0000 0.0109 -0.0335 0.195 + 86 6.7314 1.6096 0.3326 0.2885 0.0670 0.2342 0.1794 0.0060 0.0000 0.0128 -0.0280 0.179 + 87 6.9144 1.5372 0.2507 0.2331 0.0688 0.1982 0.1518 0.0045 0.0000 0.0138 -0.0212 0.159 + 88 7.0535 1.4822 0.1746 0.1713 0.0702 0.1511 0.1157 0.0028 0.0000 0.0129 -0.0142 0.139 + 89 7.1471 1.4451 0.1029 0.1047 0.0712 0.0948 0.0726 0.0012 0.0000 0.0094 -0.0078 0.121 + 90 7.1941 1.4265 0.0340 0.0353 0.0718 0.0324 0.0248 -0.0004 0.0000 0.0035 -0.0025 0.111 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02660 Clsurf = 0.00285 - CYsurf = 0.00425 Cmsurf = -0.13013 - CDsurf = 0.00157 Cnsurf = -0.00242 - CDisurf = 0.00157 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02645 Clsurf = 0.00284 + CYsurf = 0.00422 Cmsurf = -0.12942 + CDsurf = 0.00156 Cnsurf = -0.00241 + CDisurf = 0.00156 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16213 CDsurf = 0.00944 + CLsurf = 0.16122 CDsurf = 0.00941 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.5643 0.0924 0.1684 0.1290 0.0418 0.0000 -0.0082 0.0354 0.314 - 92 -0.0418 4.2566 0.2392 0.5172 0.0926 0.1579 0.1210 0.0116 0.0000 -0.0080 0.0330 0.316 - 93 -0.1156 4.2274 0.3930 0.5139 0.0926 0.1582 0.1212 0.0097 0.0000 -0.0076 0.0327 0.313 - 94 -0.2254 4.1839 0.5386 0.5131 0.0921 0.1596 0.1223 0.0093 0.0000 -0.0070 0.0324 0.307 - 95 -0.3698 4.1268 0.6730 0.5130 0.0912 0.1618 0.1240 0.0092 0.0000 -0.0062 0.0321 0.300 - 96 -0.5474 4.0565 0.7936 0.5130 0.0896 0.1647 0.1261 0.0091 0.0000 -0.0054 0.0319 0.293 - 97 -0.7617 3.9717 0.9441 0.5125 0.0873 0.1681 0.1287 0.0091 0.0000 -0.0046 0.0318 0.286 - 98 -1.0116 3.8728 1.0344 0.5120 0.0841 0.1722 0.1319 0.0091 0.0000 -0.0039 0.0318 0.279 - 99 -1.2891 3.7630 1.1046 0.5112 0.0801 0.1770 0.1355 0.0092 0.0000 -0.0032 0.0321 0.274 - 100 -1.5912 3.6435 1.1542 0.5103 0.0757 0.1825 0.1398 0.0092 0.0000 -0.0027 0.0325 0.269 - 101 -1.9146 3.5155 1.1831 0.5094 0.0713 0.1888 0.1446 0.0094 0.0000 -0.0022 0.0332 0.265 - 102 -2.2558 3.3805 1.1921 0.5085 0.0673 0.1960 0.1501 0.0095 0.0000 -0.0018 0.0341 0.262 - 103 -2.6109 3.2400 1.1821 0.5076 0.0641 0.2042 0.1564 0.0097 0.0000 -0.0015 0.0351 0.259 - 104 -2.9762 3.0955 1.1548 0.5067 0.0615 0.2134 0.1634 0.0099 0.0000 -0.0011 0.0363 0.257 - 105 -3.3476 2.9485 1.1122 0.5052 0.0596 0.2234 0.1711 0.0100 0.0000 -0.0007 0.0376 0.254 - 106 -3.7210 2.8008 1.0564 0.5027 0.0583 0.2341 0.1793 0.0101 0.0000 -0.0002 0.0390 0.251 - 107 -4.0924 2.6538 0.9900 0.4985 0.0574 0.2450 0.1877 0.0102 0.0000 0.0003 0.0404 0.249 - 108 -4.4577 2.5093 0.9155 0.4921 0.0569 0.2558 0.1960 0.0103 0.0000 0.0009 0.0417 0.246 - 109 -4.8128 2.3687 0.8353 0.4826 0.0569 0.2658 0.2036 0.0102 0.0000 0.0016 0.0427 0.242 - 110 -5.1540 2.2338 0.7518 0.4696 0.0574 0.2744 0.2101 0.0101 0.0000 0.0025 0.0433 0.238 - 111 -5.4774 2.1058 0.6671 0.4526 0.0583 0.2805 0.2149 0.0099 0.0000 0.0037 0.0434 0.233 - 112 -5.7795 1.9862 0.5830 0.4307 0.0596 0.2831 0.2168 0.0094 0.0000 0.0051 0.0426 0.226 - 113 -6.0570 1.8764 0.5012 0.4040 0.0612 0.2811 0.2153 0.0089 0.0000 0.0069 0.0408 0.218 - 114 -6.3069 1.7776 0.4225 0.3717 0.0631 0.2731 0.2092 0.0081 0.0000 0.0089 0.0378 0.208 - 115 -6.5264 1.6907 0.3478 0.3341 0.0650 0.2582 0.1977 0.0072 0.0000 0.0109 0.0336 0.195 - 116 -6.7314 1.6096 0.3326 0.2889 0.0670 0.2346 0.1797 0.0060 0.0000 0.0128 0.0281 0.179 - 117 -6.9144 1.5372 0.2507 0.2334 0.0688 0.1985 0.1520 0.0045 0.0000 0.0138 0.0213 0.159 - 118 -7.0535 1.4822 0.1746 0.1715 0.0702 0.1513 0.1159 0.0028 0.0000 0.0129 0.0142 0.139 - 119 -7.1471 1.4451 0.1029 0.1048 0.0712 0.0950 0.0727 0.0012 0.0000 0.0094 0.0078 0.121 - 120 -7.1941 1.4265 0.0340 0.0353 0.0718 0.0325 0.0249 -0.0004 0.0000 0.0035 0.0025 0.111 + 91 -0.0047 4.2713 0.0803 0.5590 0.0925 0.1668 0.1278 0.0412 0.0000 -0.0082 0.0351 0.314 + 92 -0.0418 4.2566 0.2392 0.5127 0.0927 0.1565 0.1199 0.0115 0.0000 -0.0080 0.0327 0.316 + 93 -0.1156 4.2274 0.3930 0.5095 0.0926 0.1568 0.1201 0.0096 0.0000 -0.0076 0.0324 0.313 + 94 -0.2254 4.1839 0.5386 0.5086 0.0922 0.1583 0.1212 0.0092 0.0000 -0.0070 0.0321 0.308 + 95 -0.3698 4.1268 0.6730 0.5087 0.0913 0.1605 0.1229 0.0091 0.0000 -0.0062 0.0319 0.301 + 96 -0.5474 4.0565 0.7936 0.5085 0.0897 0.1632 0.1250 0.0091 0.0000 -0.0054 0.0316 0.293 + 97 -0.7617 3.9717 0.9441 0.5083 0.0874 0.1667 0.1277 0.0090 0.0000 -0.0046 0.0315 0.286 + 98 -1.0116 3.8728 1.0344 0.5076 0.0842 0.1707 0.1308 0.0090 0.0000 -0.0039 0.0316 0.280 + 99 -1.2891 3.7630 1.1046 0.5070 0.0802 0.1755 0.1344 0.0091 0.0000 -0.0032 0.0318 0.274 + 100 -1.5912 3.6435 1.1542 0.5062 0.0758 0.1810 0.1387 0.0092 0.0000 -0.0027 0.0323 0.269 + 101 -1.9146 3.5155 1.1831 0.5054 0.0714 0.1873 0.1435 0.0093 0.0000 -0.0022 0.0330 0.266 + 102 -2.2558 3.3805 1.1921 0.5047 0.0675 0.1946 0.1490 0.0094 0.0000 -0.0018 0.0338 0.262 + 103 -2.6109 3.2400 1.1821 0.5042 0.0642 0.2029 0.1554 0.0096 0.0000 -0.0015 0.0349 0.260 + 104 -2.9762 3.0955 1.1548 0.5035 0.0617 0.2121 0.1624 0.0098 0.0000 -0.0011 0.0361 0.257 + 105 -3.3476 2.9485 1.1122 0.5023 0.0598 0.2221 0.1701 0.0100 0.0000 -0.0007 0.0374 0.254 + 106 -3.7210 2.8008 1.0564 0.5000 0.0584 0.2328 0.1783 0.0101 0.0000 -0.0003 0.0388 0.252 + 107 -4.0924 2.6538 0.9900 0.4962 0.0575 0.2439 0.1868 0.0102 0.0000 0.0002 0.0402 0.249 + 108 -4.4577 2.5093 0.9155 0.4901 0.0570 0.2548 0.1951 0.0102 0.0000 0.0009 0.0415 0.246 + 109 -4.8128 2.3687 0.8353 0.4809 0.0570 0.2649 0.2029 0.0102 0.0000 0.0016 0.0425 0.242 + 110 -5.1540 2.2338 0.7518 0.4682 0.0574 0.2735 0.2095 0.0101 0.0000 0.0025 0.0432 0.238 + 111 -5.4774 2.1058 0.6671 0.4513 0.0583 0.2797 0.2143 0.0099 0.0000 0.0037 0.0433 0.233 + 112 -5.7795 1.9862 0.5830 0.4297 0.0596 0.2824 0.2163 0.0094 0.0000 0.0051 0.0425 0.226 + 113 -6.0570 1.8764 0.5012 0.4031 0.0613 0.2805 0.2149 0.0089 0.0000 0.0069 0.0407 0.218 + 114 -6.3069 1.7776 0.4225 0.3711 0.0632 0.2727 0.2089 0.0081 0.0000 0.0089 0.0377 0.208 + 115 -6.5264 1.6907 0.3478 0.3337 0.0651 0.2578 0.1975 0.0072 0.0000 0.0109 0.0335 0.195 + 116 -6.7314 1.6096 0.3326 0.2885 0.0670 0.2342 0.1794 0.0060 0.0000 0.0128 0.0280 0.179 + 117 -6.9144 1.5372 0.2507 0.2331 0.0688 0.1982 0.1518 0.0045 0.0000 0.0138 0.0212 0.159 + 118 -7.0535 1.4822 0.1746 0.1713 0.0702 0.1511 0.1157 0.0028 0.0000 0.0129 0.0142 0.139 + 119 -7.1471 1.4451 0.1029 0.1047 0.0712 0.0948 0.0726 0.0012 0.0000 0.0094 0.0078 0.121 + 120 -7.1941 1.4265 0.0340 0.0353 0.0718 0.0324 0.0248 -0.0004 0.0000 0.0035 0.0025 0.111 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.356 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.363 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.373 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.380 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.384 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.384 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.380 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.370 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.351 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.312 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.278 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.271 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.368 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.374 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.379 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.395 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.395 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.386 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.386 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.362 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.346 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.311 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.271 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.264 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.264 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.258 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.253 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.247 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.242 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.255 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.246 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.198 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.183 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.165 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.140 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.104 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.185 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.164 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.143 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.125 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.110 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00626 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.04602 + CLsurf = 0.00619 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.04610 CDsurf = -0.00021 Cnsurf = -0.00000 CDisurf = -0.00021 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00631 CDsurf = -0.00021 + CLsurf = 0.00624 CDsurf = -0.00021 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.1372 0.1282 0.0620 0.0053 -0.0020 0.0000 0.0036 0.0003 -0.416 - 152 -1.3090 31.2096 11.6724 0.2002 0.1398 0.0248 0.0065 -0.0007 0.0000 0.0043 0.0007 -0.416 - 153 -0.9350 34.0626 12.7394 0.2222 0.1329 0.0159 0.0066 -0.0001 0.0000 0.0051 0.0011 -0.521 - 154 -0.5610 36.1619 13.5246 0.2353 0.1317 0.0109 0.0065 0.0003 0.0000 0.0054 0.0017 -0.578 - 155 -0.1870 37.5332 14.0374 0.2429 0.1329 0.0074 0.0064 0.0009 0.0000 0.0055 0.0027 -0.602 - 156 0.1870 37.5332 14.0374 0.2429 0.1329 0.0074 0.0064 0.0009 0.0000 0.0055 0.0027 -0.602 - 157 0.5610 36.1619 13.5246 0.2353 0.1317 0.0109 0.0065 0.0003 0.0000 0.0054 0.0017 -0.578 - 158 0.9350 34.0626 12.7394 0.2222 0.1329 0.0159 0.0066 -0.0001 0.0000 0.0051 0.0011 -0.521 - 159 1.3090 31.2096 11.6724 0.2002 0.1398 0.0248 0.0065 -0.0007 0.0000 0.0043 0.0007 -0.416 - 160 1.6830 26.5957 9.9468 0.1372 0.1282 0.0620 0.0053 -0.0020 0.0000 0.0036 0.0003 -0.416 + 151 -1.6830 26.5957 9.9468 0.1353 0.1282 0.0612 0.0053 -0.0020 0.0000 0.0036 0.0003 -0.429 + 152 -1.3090 31.2096 11.6724 0.1977 0.1398 0.0245 0.0064 -0.0007 0.0000 0.0044 0.0007 -0.428 + 153 -0.9350 34.0626 12.7394 0.2197 0.1330 0.0157 0.0065 -0.0001 0.0000 0.0051 0.0012 -0.533 + 154 -0.5610 36.1619 13.5246 0.2328 0.1319 0.0108 0.0064 0.0003 0.0000 0.0054 0.0017 -0.590 + 155 -0.1870 37.5332 14.0374 0.2404 0.1331 0.0074 0.0064 0.0009 0.0000 0.0055 0.0027 -0.613 + 156 0.1870 37.5332 14.0374 0.2404 0.1331 0.0074 0.0064 0.0009 0.0000 0.0055 0.0027 -0.613 + 157 0.5610 36.1619 13.5246 0.2328 0.1319 0.0108 0.0064 0.0003 0.0000 0.0054 0.0017 -0.590 + 158 0.9350 34.0626 12.7394 0.2197 0.1330 0.0157 0.0065 -0.0001 0.0000 0.0051 0.0012 -0.533 + 159 1.3090 31.2096 11.6724 0.1977 0.1398 0.0245 0.0064 -0.0007 0.0000 0.0044 0.0007 -0.428 + 160 1.6830 26.5957 9.9468 0.1353 0.1282 0.0612 0.0053 -0.0020 0.0000 0.0036 0.0003 -0.429 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = 0.00000 Clsurf = -0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + CDsurf = -0.00000 Cnsurf = -0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = 0.00000 + CLsurf = -0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.860 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.267 - 163 0.0000 34.0626 12.7394 -0.0000 0.0001 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.033 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.077 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.176 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.408 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.483 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.553 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.615 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.694 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.093 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.658 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.042 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.122 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.185 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.431 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.522 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.572 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.630 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.697 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_04_05.txt b/regression/scripts/AVL/avl_files/strip_forces_case_04_05.txt index fac374e46f..f12181e139 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_04_05.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_04_05.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.40163 Clsurf = -0.07858 - CYsurf = -0.02228 Cmsurf = -0.36312 - CDsurf = 0.01425 Cnsurf = -0.00746 - CDisurf = 0.01425 CDvsurf = 0.00000 + CLsurf = 0.40214 Clsurf = -0.07863 + CYsurf = -0.02196 Cmsurf = -0.36337 + CDsurf = 0.01372 Cnsurf = -0.00751 + CDisurf = 0.01372 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.78508 CDsurf = 0.02782 + CLsurf = 0.78604 CDsurf = 0.02678 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 5.1641 0.1766 0.7582 0.5873 0.6820 0.0000 -0.0366 -0.1668 0.312 - 2 0.1025 7.6885 1.0492 4.6952 0.1762 0.7736 0.5992 0.1307 0.0000 -0.0366 -0.1555 0.311 - 3 0.2837 7.5620 1.7073 4.6549 0.1749 0.7855 0.6084 0.0962 0.0000 -0.0342 -0.1546 0.306 - 4 0.5530 7.3741 2.3052 4.6329 0.1720 0.8036 0.6224 0.0861 0.0000 -0.0305 -0.1542 0.299 - 5 0.9075 7.1267 2.8223 4.5983 0.1661 0.8272 0.6407 0.0764 0.0000 -0.0264 -0.1544 0.291 - 6 1.3432 6.8226 3.2414 4.5408 0.1535 0.8546 0.6619 0.0699 0.0000 -0.0226 -0.1555 0.284 - 7 1.8554 6.4651 3.5491 4.4615 0.1283 0.8877 0.6875 0.0629 0.0000 -0.0194 -0.1580 0.278 - 8 2.4386 6.0582 3.7368 4.3275 0.1030 0.9216 0.7138 0.0477 0.0000 -0.0178 -0.1617 0.275 - 9 3.0862 5.6062 3.8005 4.1672 0.0894 0.9606 0.7440 0.0397 0.0000 -0.0172 -0.1671 0.273 - 10 3.7613 5.1351 3.4440 3.9776 0.0777 1.0029 0.7767 0.0299 0.0000 -0.0181 -0.1743 0.273 - 11 4.4532 4.6522 3.3149 3.7703 0.0636 1.0514 0.8143 0.0179 0.0000 -0.0203 -0.1835 0.275 - 12 5.1831 4.1429 3.0930 3.5465 0.0420 1.1131 0.8620 0.0035 0.0000 -0.0227 -0.1948 0.276 - 13 6.0123 3.7903 3.4706 3.3079 0.0272 1.0797 0.8797 -0.0036 0.0000 -0.0201 -0.2152 0.273 - 14 6.9353 3.6075 3.3775 3.1239 0.0255 1.0710 0.8726 -0.0012 0.0000 -0.0202 -0.2137 0.273 - 15 7.8737 3.4215 3.2389 2.9568 0.0218 1.0688 0.8708 -0.0011 0.0000 -0.0200 -0.2131 0.273 - 16 8.8172 3.2345 3.0619 2.7981 0.0195 1.0700 0.8718 -0.0017 0.0000 -0.0197 -0.2131 0.273 - 17 9.7556 3.0486 2.8543 2.6427 0.0191 1.0723 0.8736 -0.0024 0.0000 -0.0194 -0.2132 0.272 - 18 10.6786 2.8657 2.6240 2.4902 0.0201 1.0750 0.8759 -0.0031 0.0000 -0.0190 -0.2134 0.272 - 19 11.5760 2.6879 2.3787 2.3395 0.0219 1.0769 0.8774 -0.0039 0.0000 -0.0185 -0.2133 0.271 - 20 12.4328 2.5181 2.1010 2.1904 0.0246 1.0764 0.8770 -0.0047 0.0000 -0.0178 -0.2125 0.270 - 21 13.2400 2.3582 1.8520 2.0415 0.0285 1.0713 0.8729 -0.0053 0.0000 -0.0166 -0.2105 0.269 - 22 13.9941 2.2087 1.6074 1.8901 0.0339 1.0591 0.8629 -0.0057 0.0000 -0.0149 -0.2067 0.267 - 23 14.6868 2.0715 1.3716 1.7320 0.0411 1.0348 0.8431 -0.0058 0.0000 -0.0121 -0.1998 0.264 - 24 15.3105 1.9479 1.1479 1.5613 0.0502 0.9920 0.8082 -0.0055 0.0000 -0.0081 -0.1885 0.260 - 25 15.8583 1.8393 0.9381 1.3694 0.0602 0.9212 0.7506 -0.0038 0.0000 -0.0042 -0.1722 0.256 - 26 16.3244 1.7470 0.7427 1.1511 0.0705 0.8143 0.6635 0.0029 0.0000 -0.0061 -0.1545 0.259 - 27 16.6722 1.4928 0.4131 0.9154 0.0814 2.0752 0.6212 -0.0265 0.0000 -0.0085 -0.0805 0.264 - 28 16.9098 1.1466 0.2292 0.6766 0.0961 2.0097 0.6016 -0.0566 0.0000 0.0165 -0.0662 0.223 - 29 17.0696 0.9138 0.1104 0.4170 0.1076 1.5696 0.4698 -0.0801 0.0000 0.0396 -0.0389 0.166 - 30 17.1499 0.7967 0.0322 0.1410 0.1133 0.6208 0.1858 -0.0598 0.0000 0.0253 -0.0105 0.114 + 1 0.0114 7.7520 0.3539 5.1830 0.1766 0.7612 0.5896 0.6829 0.0000 -0.0383 -0.1687 0.315 + 2 0.1025 7.6885 1.0491 4.7113 0.1763 0.7763 0.6013 0.1307 0.0000 -0.0379 -0.1570 0.313 + 3 0.2837 7.5620 1.7073 4.6713 0.1752 0.7882 0.6105 0.0964 0.0000 -0.0356 -0.1561 0.308 + 4 0.5530 7.3741 2.3052 4.6469 0.1725 0.8065 0.6247 0.0831 0.0000 -0.0319 -0.1557 0.301 + 5 0.9075 7.1267 2.8223 4.6137 0.1667 0.8296 0.6426 0.0786 0.0000 -0.0278 -0.1559 0.293 + 6 1.3432 6.8226 3.2414 4.5548 0.1542 0.8577 0.6643 0.0675 0.0000 -0.0240 -0.1570 0.286 + 7 1.8554 6.4651 3.5491 4.4645 0.1289 0.8899 0.6892 0.0529 0.0000 -0.0210 -0.1593 0.280 + 8 2.4386 6.0582 3.7368 4.3425 0.1037 0.9250 0.7165 0.0466 0.0000 -0.0189 -0.1630 0.276 + 9 3.0862 5.6062 3.8005 4.1896 0.0904 0.9660 0.7482 0.0382 0.0000 -0.0178 -0.1685 0.274 + 10 3.7613 5.1351 3.4440 3.9618 0.0784 0.9992 0.7739 0.0280 0.0000 -0.0200 -0.1752 0.276 + 11 4.4532 4.6522 3.3149 3.7738 0.0635 1.0526 0.8152 0.0171 0.0000 -0.0203 -0.1836 0.275 + 12 5.1831 4.1429 3.0930 3.5460 0.0413 1.1130 0.8620 0.0027 0.0000 -0.0216 -0.1939 0.275 + 13 6.0123 3.7903 3.4706 3.3108 0.0267 1.0807 0.8805 -0.0035 0.0000 -0.0186 -0.2140 0.271 + 14 6.9353 3.6075 3.3775 3.1262 0.0252 1.0718 0.8733 -0.0013 0.0000 -0.0185 -0.2124 0.271 + 15 7.8737 3.4215 3.2389 2.9582 0.0217 1.0693 0.8712 -0.0011 0.0000 -0.0183 -0.2118 0.271 + 16 8.8172 3.2345 3.0619 2.7996 0.0194 1.0706 0.8722 -0.0017 0.0000 -0.0180 -0.2117 0.271 + 17 9.7556 3.0486 2.8543 2.6441 0.0190 1.0729 0.8741 -0.0025 0.0000 -0.0177 -0.2118 0.270 + 18 10.6786 2.8657 2.6239 2.4914 0.0200 1.0756 0.8763 -0.0032 0.0000 -0.0173 -0.2120 0.270 + 19 11.5760 2.6879 2.3787 2.3405 0.0219 1.0774 0.8778 -0.0040 0.0000 -0.0168 -0.2118 0.269 + 20 12.4328 2.5181 2.1010 2.1912 0.0246 1.0768 0.8773 -0.0048 0.0000 -0.0160 -0.2110 0.268 + 21 13.2400 2.3582 1.8520 2.0422 0.0285 1.0717 0.8732 -0.0054 0.0000 -0.0149 -0.2091 0.267 + 22 13.9941 2.2087 1.6074 1.8906 0.0338 1.0594 0.8631 -0.0058 0.0000 -0.0131 -0.2052 0.265 + 23 14.6868 2.0715 1.3716 1.7324 0.0411 1.0350 0.8433 -0.0059 0.0000 -0.0103 -0.1983 0.262 + 24 15.3105 1.9479 1.1479 1.5613 0.0501 0.9920 0.8082 -0.0056 0.0000 -0.0064 -0.1870 0.258 + 25 15.8583 1.8393 0.9381 1.3694 0.0601 0.9213 0.7506 -0.0039 0.0000 -0.0025 -0.1707 0.253 + 26 16.3244 1.7470 0.7427 1.1506 0.0701 0.8140 0.6632 0.0028 0.0000 -0.0044 -0.1529 0.257 + 27 16.6722 1.4928 0.4131 0.9149 0.0811 2.0743 0.6209 -0.0267 0.0000 -0.0071 -0.0798 0.261 + 28 16.9098 1.1466 0.2292 0.6764 0.0960 2.0092 0.6014 -0.0568 0.0000 0.0175 -0.0657 0.221 + 29 17.0696 0.9138 0.1104 0.4170 0.1077 1.5697 0.4699 -0.0804 0.0000 0.0402 -0.0386 0.164 + 30 17.1499 0.7967 0.0322 0.1411 0.1141 0.6212 0.1859 -0.0603 0.0000 0.0255 -0.0105 0.113 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.40162 Clsurf = 0.07858 - CYsurf = 0.02228 Cmsurf = -0.36312 - CDsurf = 0.01425 Cnsurf = 0.00746 - CDisurf = 0.01425 CDvsurf = 0.00000 + CLsurf = 0.40214 Clsurf = 0.07863 + CYsurf = 0.02196 Cmsurf = -0.36337 + CDsurf = 0.01372 Cnsurf = 0.00751 + CDisurf = 0.01372 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.78507 CDsurf = 0.02782 + CLsurf = 0.78604 CDsurf = 0.02678 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 5.1641 0.1767 0.7582 0.5872 0.6821 0.0000 -0.0366 0.1668 0.312 - 32 -0.1025 7.6885 1.0492 4.6952 0.1762 0.7736 0.5992 0.1307 0.0000 -0.0366 0.1555 0.311 - 33 -0.2837 7.5620 1.7073 4.6549 0.1749 0.7855 0.6084 0.0962 0.0000 -0.0342 0.1546 0.306 - 34 -0.5530 7.3741 2.3052 4.6329 0.1720 0.8036 0.6224 0.0861 0.0000 -0.0305 0.1542 0.299 - 35 -0.9075 7.1267 2.8223 4.5983 0.1661 0.8272 0.6407 0.0764 0.0000 -0.0264 0.1544 0.291 - 36 -1.3432 6.8226 3.2414 4.5408 0.1535 0.8546 0.6619 0.0699 0.0000 -0.0226 0.1555 0.284 - 37 -1.8554 6.4651 3.5491 4.4615 0.1283 0.8877 0.6875 0.0629 0.0000 -0.0194 0.1580 0.278 - 38 -2.4386 6.0582 3.7368 4.3275 0.1030 0.9216 0.7138 0.0477 0.0000 -0.0178 0.1617 0.275 - 39 -3.0862 5.6062 3.8005 4.1672 0.0894 0.9606 0.7440 0.0397 0.0000 -0.0172 0.1671 0.273 - 40 -3.7613 5.1351 3.4440 3.9776 0.0777 1.0029 0.7767 0.0299 0.0000 -0.0181 0.1743 0.273 - 41 -4.4532 4.6522 3.3149 3.7702 0.0636 1.0514 0.8143 0.0179 0.0000 -0.0203 0.1835 0.275 - 42 -5.1831 4.1429 3.0930 3.5465 0.0420 1.1131 0.8620 0.0035 0.0000 -0.0227 0.1948 0.276 - 43 -6.0123 3.7903 3.4706 3.3078 0.0272 1.0797 0.8797 -0.0036 0.0000 -0.0201 0.2152 0.273 - 44 -6.9353 3.6075 3.3775 3.1239 0.0255 1.0710 0.8726 -0.0012 0.0000 -0.0202 0.2137 0.273 - 45 -7.8737 3.4215 3.2389 2.9567 0.0218 1.0688 0.8708 -0.0011 0.0000 -0.0200 0.2131 0.273 - 46 -8.8172 3.2345 3.0619 2.7981 0.0195 1.0700 0.8718 -0.0017 0.0000 -0.0197 0.2131 0.273 - 47 -9.7556 3.0486 2.8543 2.6426 0.0191 1.0723 0.8736 -0.0024 0.0000 -0.0194 0.2132 0.272 - 48 -10.6786 2.8657 2.6240 2.4902 0.0201 1.0750 0.8759 -0.0031 0.0000 -0.0190 0.2134 0.272 - 49 -11.5760 2.6879 2.3787 2.3395 0.0219 1.0769 0.8774 -0.0039 0.0000 -0.0185 0.2133 0.271 - 50 -12.4328 2.5181 2.1010 2.1903 0.0246 1.0763 0.8769 -0.0047 0.0000 -0.0178 0.2125 0.270 - 51 -13.2400 2.3582 1.8520 2.0415 0.0285 1.0713 0.8729 -0.0053 0.0000 -0.0166 0.2105 0.269 - 52 -13.9941 2.2087 1.6074 1.8901 0.0339 1.0591 0.8629 -0.0057 0.0000 -0.0149 0.2067 0.267 - 53 -14.6868 2.0715 1.3716 1.7320 0.0411 1.0348 0.8431 -0.0058 0.0000 -0.0121 0.1998 0.264 - 54 -15.3105 1.9479 1.1479 1.5612 0.0502 0.9920 0.8082 -0.0055 0.0000 -0.0081 0.1885 0.260 - 55 -15.8583 1.8393 0.9381 1.3694 0.0602 0.9212 0.7506 -0.0038 0.0000 -0.0042 0.1722 0.256 - 56 -16.3244 1.7470 0.7427 1.1510 0.0705 0.8143 0.6635 0.0029 0.0000 -0.0061 0.1545 0.259 - 57 -16.6722 1.4928 0.4131 0.9154 0.0814 2.0752 0.6212 -0.0265 0.0000 -0.0085 0.0805 0.264 - 58 -16.9098 1.1466 0.2292 0.6766 0.0961 2.0096 0.6016 -0.0566 0.0000 0.0165 0.0662 0.223 - 59 -17.0696 0.9138 0.1104 0.4170 0.1076 1.5696 0.4698 -0.0801 0.0000 0.0396 0.0389 0.166 - 60 -17.1499 0.7967 0.0322 0.1410 0.1133 0.6208 0.1858 -0.0598 0.0000 0.0253 0.0105 0.114 + 31 -0.0114 7.7520 0.3539 5.1830 0.1766 0.7612 0.5896 0.6829 0.0000 -0.0383 0.1687 0.315 + 32 -0.1025 7.6885 1.0491 4.7113 0.1763 0.7763 0.6013 0.1307 0.0000 -0.0379 0.1570 0.313 + 33 -0.2837 7.5620 1.7073 4.6713 0.1752 0.7882 0.6105 0.0964 0.0000 -0.0356 0.1561 0.308 + 34 -0.5530 7.3741 2.3052 4.6469 0.1725 0.8065 0.6247 0.0831 0.0000 -0.0319 0.1557 0.301 + 35 -0.9075 7.1267 2.8223 4.6137 0.1667 0.8296 0.6426 0.0786 0.0000 -0.0278 0.1559 0.293 + 36 -1.3432 6.8226 3.2414 4.5548 0.1542 0.8577 0.6643 0.0675 0.0000 -0.0240 0.1570 0.286 + 37 -1.8554 6.4651 3.5491 4.4645 0.1289 0.8899 0.6892 0.0529 0.0000 -0.0210 0.1593 0.280 + 38 -2.4386 6.0582 3.7368 4.3425 0.1037 0.9250 0.7165 0.0466 0.0000 -0.0189 0.1630 0.276 + 39 -3.0862 5.6062 3.8005 4.1896 0.0904 0.9660 0.7482 0.0382 0.0000 -0.0178 0.1685 0.274 + 40 -3.7613 5.1351 3.4440 3.9618 0.0784 0.9992 0.7739 0.0280 0.0000 -0.0200 0.1752 0.276 + 41 -4.4532 4.6522 3.3149 3.7738 0.0635 1.0526 0.8152 0.0171 0.0000 -0.0203 0.1836 0.275 + 42 -5.1831 4.1429 3.0930 3.5460 0.0413 1.1130 0.8620 0.0027 0.0000 -0.0216 0.1939 0.275 + 43 -6.0123 3.7903 3.4706 3.3108 0.0267 1.0807 0.8805 -0.0035 0.0000 -0.0186 0.2140 0.271 + 44 -6.9353 3.6075 3.3775 3.1262 0.0252 1.0718 0.8733 -0.0013 0.0000 -0.0185 0.2124 0.271 + 45 -7.8737 3.4215 3.2389 2.9582 0.0217 1.0693 0.8712 -0.0011 0.0000 -0.0183 0.2118 0.271 + 46 -8.8172 3.2345 3.0619 2.7996 0.0194 1.0706 0.8722 -0.0017 0.0000 -0.0180 0.2117 0.271 + 47 -9.7556 3.0486 2.8543 2.6441 0.0190 1.0729 0.8741 -0.0025 0.0000 -0.0177 0.2118 0.270 + 48 -10.6786 2.8657 2.6239 2.4914 0.0200 1.0756 0.8763 -0.0032 0.0000 -0.0173 0.2120 0.270 + 49 -11.5760 2.6879 2.3787 2.3405 0.0219 1.0774 0.8778 -0.0040 0.0000 -0.0168 0.2118 0.269 + 50 -12.4328 2.5181 2.1010 2.1912 0.0246 1.0768 0.8773 -0.0048 0.0000 -0.0160 0.2110 0.268 + 51 -13.2400 2.3582 1.8520 2.0422 0.0285 1.0717 0.8732 -0.0054 0.0000 -0.0149 0.2091 0.267 + 52 -13.9941 2.2087 1.6074 1.8906 0.0338 1.0594 0.8631 -0.0058 0.0000 -0.0131 0.2052 0.265 + 53 -14.6868 2.0715 1.3716 1.7324 0.0411 1.0350 0.8433 -0.0059 0.0000 -0.0103 0.1983 0.262 + 54 -15.3105 1.9479 1.1479 1.5613 0.0501 0.9920 0.8082 -0.0056 0.0000 -0.0064 0.1870 0.258 + 55 -15.8583 1.8393 0.9381 1.3694 0.0601 0.9213 0.7506 -0.0039 0.0000 -0.0025 0.1707 0.253 + 56 -16.3244 1.7470 0.7427 1.1506 0.0701 0.8140 0.6632 0.0028 0.0000 -0.0044 0.1529 0.257 + 57 -16.6722 1.4928 0.4131 0.9149 0.0811 2.0742 0.6209 -0.0267 0.0000 -0.0071 0.0798 0.261 + 58 -16.9098 1.1466 0.2292 0.6764 0.0960 2.0092 0.6014 -0.0568 0.0000 0.0175 0.0657 0.221 + 59 -17.0696 0.9138 0.1104 0.4170 0.1077 1.5697 0.4699 -0.0804 0.0000 0.0402 0.0386 0.164 + 60 -17.1499 0.7967 0.0322 0.1411 0.1141 0.6212 0.1859 -0.0603 0.0000 0.0255 0.0105 0.113 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04256 Clsurf = -0.00446 - CYsurf = -0.00679 Cmsurf = -0.20831 - CDsurf = 0.00330 Cnsurf = 0.00376 - CDisurf = 0.00330 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04241 Clsurf = -0.00444 + CYsurf = -0.00677 Cmsurf = -0.20758 + CDsurf = 0.00329 Cnsurf = 0.00375 + CDisurf = 0.00329 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25938 CDsurf = 0.01986 + CLsurf = 0.25846 CDsurf = 0.01981 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.0037 0.1246 0.2919 0.2228 0.1136 0.0000 -0.0127 -0.0617 0.307 - 62 0.0418 4.2566 0.2392 0.8707 0.1250 0.2655 0.2027 0.0278 0.0000 -0.0124 -0.0550 0.311 - 63 0.1156 4.2274 0.3930 0.8611 0.1251 0.2653 0.2025 0.0222 0.0000 -0.0118 -0.0543 0.308 - 64 0.2254 4.1839 0.5386 0.8583 0.1246 0.2674 0.2041 0.0210 0.0000 -0.0107 -0.0537 0.303 - 65 0.3698 4.1268 0.6730 0.8576 0.1234 0.2710 0.2068 0.0206 0.0000 -0.0094 -0.0532 0.296 - 66 0.5474 4.0565 0.7936 0.8569 0.1214 0.2756 0.2103 0.0203 0.0000 -0.0080 -0.0528 0.288 - 67 0.7617 3.9717 0.9441 0.8549 0.1182 0.2809 0.2144 0.0200 0.0000 -0.0066 -0.0525 0.281 - 68 1.0116 3.8728 1.0344 0.8529 0.1137 0.2875 0.2194 0.0198 0.0000 -0.0054 -0.0526 0.275 - 69 1.2891 3.7630 1.1046 0.8495 0.1081 0.2948 0.2250 0.0199 0.0000 -0.0043 -0.0529 0.269 - 70 1.5912 3.6435 1.1542 0.8456 0.1017 0.3032 0.2314 0.0199 0.0000 -0.0034 -0.0535 0.265 - 71 1.9146 3.5155 1.1831 0.8408 0.0954 0.3125 0.2385 0.0200 0.0000 -0.0026 -0.0544 0.261 - 72 2.2558 3.3805 1.1921 0.8347 0.0898 0.3227 0.2463 0.0201 0.0000 -0.0019 -0.0555 0.258 - 73 2.6109 3.2400 1.1821 0.8282 0.0853 0.3342 0.2550 0.0203 0.0000 -0.0013 -0.0569 0.255 - 74 2.9762 3.0955 1.1548 0.8207 0.0819 0.3467 0.2646 0.0205 0.0000 -0.0008 -0.0585 0.253 - 75 3.3476 2.9485 1.1122 0.8117 0.0796 0.3601 0.2748 0.0205 0.0000 -0.0002 -0.0602 0.251 - 76 3.7210 2.8008 1.0564 0.8011 0.0780 0.3742 0.2856 0.0207 0.0000 0.0005 -0.0620 0.248 - 77 4.0924 2.6538 0.9900 0.7874 0.0770 0.3883 0.2964 0.0207 0.0000 0.0012 -0.0638 0.246 - 78 4.4577 2.5093 0.9155 0.7707 0.0766 0.4021 0.3069 0.0207 0.0000 0.0021 -0.0653 0.243 - 79 4.8128 2.3687 0.8353 0.7495 0.0769 0.4144 0.3163 0.0204 0.0000 0.0031 -0.0665 0.240 - 80 5.1540 2.2338 0.7518 0.7239 0.0778 0.4246 0.3240 0.0200 0.0000 0.0044 -0.0670 0.236 - 81 5.4774 2.1058 0.6671 0.6930 0.0793 0.4313 0.3291 0.0194 0.0000 0.0061 -0.0667 0.231 - 82 5.7795 1.9862 0.5830 0.6553 0.0814 0.4326 0.3301 0.0183 0.0000 0.0082 -0.0652 0.225 - 83 6.0570 1.8764 0.5012 0.6117 0.0839 0.4275 0.3263 0.0171 0.0000 0.0107 -0.0622 0.217 - 84 6.3069 1.7776 0.4225 0.5603 0.0868 0.4136 0.3156 0.0157 0.0000 0.0136 -0.0575 0.207 - 85 6.5264 1.6907 0.3478 0.5019 0.0897 0.3896 0.2974 0.0136 0.0000 0.0166 -0.0510 0.194 - 86 6.7314 1.6096 0.3326 0.4327 0.0926 0.3531 0.2694 0.0114 0.0000 0.0193 -0.0426 0.178 - 87 6.9144 1.5372 0.2507 0.3486 0.0953 0.2981 0.2275 0.0083 0.0000 0.0207 -0.0322 0.159 - 88 7.0535 1.4822 0.1746 0.2556 0.0975 0.2268 0.1731 0.0049 0.0000 0.0193 -0.0215 0.139 - 89 7.1471 1.4451 0.1029 0.1561 0.0990 0.1423 0.1086 0.0019 0.0000 0.0140 -0.0119 0.121 + 61 0.0047 4.2713 0.0803 0.9978 0.1247 0.2902 0.2215 0.1126 0.0000 -0.0127 -0.0613 0.307 + 62 0.0418 4.2566 0.2392 0.8662 0.1251 0.2642 0.2016 0.0277 0.0000 -0.0124 -0.0547 0.311 + 63 0.1156 4.2274 0.3930 0.8566 0.1252 0.2639 0.2014 0.0221 0.0000 -0.0118 -0.0540 0.308 + 64 0.2254 4.1839 0.5386 0.8538 0.1247 0.2660 0.2030 0.0208 0.0000 -0.0107 -0.0535 0.303 + 65 0.3698 4.1268 0.6730 0.8533 0.1235 0.2697 0.2058 0.0204 0.0000 -0.0094 -0.0530 0.296 + 66 0.5474 4.0565 0.7936 0.8522 0.1215 0.2740 0.2092 0.0202 0.0000 -0.0080 -0.0525 0.288 + 67 0.7617 3.9717 0.9441 0.8510 0.1183 0.2796 0.2134 0.0200 0.0000 -0.0066 -0.0523 0.281 + 68 1.0116 3.8728 1.0344 0.8482 0.1138 0.2859 0.2182 0.0197 0.0000 -0.0054 -0.0523 0.275 + 69 1.2891 3.7630 1.1046 0.8452 0.1082 0.2933 0.2239 0.0198 0.0000 -0.0043 -0.0526 0.269 + 70 1.5912 3.6435 1.1542 0.8414 0.1019 0.3017 0.2302 0.0198 0.0000 -0.0034 -0.0532 0.265 + 71 1.9146 3.5155 1.1831 0.8366 0.0955 0.3109 0.2373 0.0199 0.0000 -0.0026 -0.0541 0.261 + 72 2.2558 3.3805 1.1921 0.8310 0.0899 0.3212 0.2452 0.0200 0.0000 -0.0019 -0.0553 0.258 + 73 2.6109 3.2400 1.1821 0.8250 0.0854 0.3328 0.2540 0.0203 0.0000 -0.0014 -0.0567 0.255 + 74 2.9762 3.0955 1.1548 0.8177 0.0821 0.3454 0.2636 0.0205 0.0000 -0.0008 -0.0583 0.253 + 75 3.3476 2.9485 1.1122 0.8088 0.0797 0.3588 0.2738 0.0206 0.0000 -0.0002 -0.0600 0.251 + 76 3.7210 2.8008 1.0564 0.7982 0.0781 0.3728 0.2846 0.0208 0.0000 0.0004 -0.0618 0.248 + 77 4.0924 2.6538 0.9900 0.7850 0.0771 0.3871 0.2955 0.0207 0.0000 0.0012 -0.0636 0.246 + 78 4.4577 2.5093 0.9155 0.7686 0.0767 0.4010 0.3060 0.0206 0.0000 0.0020 -0.0651 0.243 + 79 4.8128 2.3687 0.8353 0.7478 0.0770 0.4135 0.3156 0.0204 0.0000 0.0031 -0.0663 0.240 + 80 5.1540 2.2338 0.7518 0.7226 0.0778 0.4238 0.3234 0.0200 0.0000 0.0044 -0.0669 0.236 + 81 5.4774 2.1058 0.6671 0.6916 0.0793 0.4304 0.3285 0.0194 0.0000 0.0061 -0.0666 0.232 + 82 5.7795 1.9862 0.5830 0.6543 0.0814 0.4319 0.3296 0.0183 0.0000 0.0081 -0.0651 0.225 + 83 6.0570 1.8764 0.5012 0.6107 0.0840 0.4269 0.3258 0.0172 0.0000 0.0107 -0.0621 0.217 + 84 6.3069 1.7776 0.4225 0.5598 0.0868 0.4132 0.3153 0.0157 0.0000 0.0136 -0.0574 0.207 + 85 6.5264 1.6907 0.3478 0.5015 0.0897 0.3893 0.2971 0.0137 0.0000 0.0166 -0.0509 0.194 + 86 6.7314 1.6096 0.3326 0.4323 0.0926 0.3527 0.2692 0.0113 0.0000 0.0193 -0.0425 0.178 + 87 6.9144 1.5372 0.2507 0.3482 0.0953 0.2977 0.2272 0.0083 0.0000 0.0207 -0.0322 0.159 + 88 7.0535 1.4822 0.1746 0.2554 0.0975 0.2267 0.1730 0.0050 0.0000 0.0193 -0.0215 0.139 + 89 7.1471 1.4451 0.1029 0.1560 0.0990 0.1422 0.1085 0.0019 0.0000 0.0140 -0.0119 0.121 90 7.1941 1.4265 0.0340 0.0525 0.0998 0.0488 0.0372 -0.0012 0.0000 0.0052 -0.0037 0.112 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04256 Clsurf = 0.00446 - CYsurf = 0.00679 Cmsurf = -0.20830 - CDsurf = 0.00330 Cnsurf = -0.00376 - CDisurf = 0.00330 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04241 Clsurf = 0.00444 + CYsurf = 0.00677 Cmsurf = -0.20758 + CDsurf = 0.00329 Cnsurf = -0.00375 + CDisurf = 0.00329 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25938 CDsurf = 0.01985 + CLsurf = 0.25846 CDsurf = 0.01981 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.0037 0.1246 0.2919 0.2228 0.1136 0.0000 -0.0127 0.0617 0.307 - 92 -0.0418 4.2566 0.2392 0.8707 0.1250 0.2655 0.2027 0.0278 0.0000 -0.0124 0.0550 0.311 - 93 -0.1156 4.2274 0.3930 0.8611 0.1251 0.2653 0.2025 0.0222 0.0000 -0.0118 0.0543 0.308 - 94 -0.2254 4.1839 0.5386 0.8583 0.1246 0.2674 0.2041 0.0210 0.0000 -0.0107 0.0537 0.303 - 95 -0.3698 4.1268 0.6730 0.8576 0.1234 0.2710 0.2068 0.0206 0.0000 -0.0094 0.0532 0.296 - 96 -0.5474 4.0565 0.7936 0.8569 0.1214 0.2756 0.2103 0.0203 0.0000 -0.0080 0.0528 0.288 - 97 -0.7617 3.9717 0.9441 0.8549 0.1182 0.2809 0.2144 0.0200 0.0000 -0.0066 0.0525 0.281 - 98 -1.0116 3.8728 1.0344 0.8529 0.1137 0.2875 0.2194 0.0198 0.0000 -0.0054 0.0526 0.275 - 99 -1.2891 3.7630 1.1046 0.8495 0.1081 0.2948 0.2250 0.0199 0.0000 -0.0043 0.0529 0.269 - 100 -1.5912 3.6435 1.1542 0.8456 0.1017 0.3032 0.2314 0.0199 0.0000 -0.0034 0.0535 0.265 - 101 -1.9146 3.5155 1.1831 0.8408 0.0954 0.3125 0.2385 0.0200 0.0000 -0.0026 0.0544 0.261 - 102 -2.2558 3.3805 1.1921 0.8347 0.0898 0.3227 0.2463 0.0201 0.0000 -0.0019 0.0555 0.258 - 103 -2.6109 3.2400 1.1821 0.8282 0.0853 0.3342 0.2550 0.0203 0.0000 -0.0013 0.0569 0.255 - 104 -2.9762 3.0955 1.1548 0.8206 0.0819 0.3467 0.2646 0.0205 0.0000 -0.0008 0.0585 0.253 - 105 -3.3476 2.9485 1.1122 0.8117 0.0796 0.3601 0.2748 0.0205 0.0000 -0.0002 0.0602 0.251 - 106 -3.7210 2.8008 1.0564 0.8010 0.0780 0.3742 0.2856 0.0207 0.0000 0.0005 0.0620 0.248 - 107 -4.0924 2.6538 0.9900 0.7874 0.0770 0.3883 0.2964 0.0207 0.0000 0.0012 0.0638 0.246 - 108 -4.4577 2.5093 0.9155 0.7707 0.0766 0.4021 0.3069 0.0207 0.0000 0.0021 0.0653 0.243 - 109 -4.8128 2.3687 0.8353 0.7495 0.0769 0.4144 0.3162 0.0204 0.0000 0.0031 0.0665 0.240 - 110 -5.1540 2.2338 0.7518 0.7239 0.0778 0.4246 0.3240 0.0200 0.0000 0.0044 0.0670 0.236 - 111 -5.4774 2.1058 0.6671 0.6930 0.0793 0.4313 0.3291 0.0194 0.0000 0.0061 0.0667 0.231 - 112 -5.7795 1.9862 0.5830 0.6553 0.0814 0.4326 0.3301 0.0183 0.0000 0.0082 0.0652 0.225 - 113 -6.0570 1.8764 0.5012 0.6117 0.0839 0.4275 0.3263 0.0171 0.0000 0.0107 0.0622 0.217 - 114 -6.3069 1.7776 0.4225 0.5603 0.0868 0.4136 0.3156 0.0157 0.0000 0.0136 0.0575 0.207 - 115 -6.5264 1.6907 0.3478 0.5019 0.0897 0.3896 0.2974 0.0136 0.0000 0.0166 0.0509 0.194 - 116 -6.7314 1.6096 0.3326 0.4327 0.0926 0.3531 0.2694 0.0114 0.0000 0.0193 0.0426 0.178 - 117 -6.9144 1.5372 0.2507 0.3486 0.0953 0.2981 0.2274 0.0083 0.0000 0.0207 0.0322 0.159 - 118 -7.0535 1.4822 0.1746 0.2556 0.0975 0.2268 0.1731 0.0049 0.0000 0.0193 0.0215 0.139 - 119 -7.1471 1.4451 0.1029 0.1561 0.0990 0.1423 0.1086 0.0019 0.0000 0.0140 0.0119 0.121 + 91 -0.0047 4.2713 0.0803 0.9978 0.1247 0.2902 0.2215 0.1126 0.0000 -0.0127 0.0613 0.307 + 92 -0.0418 4.2566 0.2392 0.8662 0.1251 0.2642 0.2016 0.0277 0.0000 -0.0124 0.0547 0.311 + 93 -0.1156 4.2274 0.3930 0.8566 0.1252 0.2639 0.2014 0.0221 0.0000 -0.0118 0.0540 0.308 + 94 -0.2254 4.1839 0.5386 0.8538 0.1247 0.2660 0.2030 0.0208 0.0000 -0.0107 0.0535 0.303 + 95 -0.3698 4.1268 0.6730 0.8533 0.1235 0.2697 0.2058 0.0204 0.0000 -0.0094 0.0530 0.296 + 96 -0.5474 4.0565 0.7936 0.8522 0.1215 0.2740 0.2092 0.0202 0.0000 -0.0080 0.0525 0.288 + 97 -0.7617 3.9717 0.9441 0.8510 0.1183 0.2796 0.2134 0.0200 0.0000 -0.0066 0.0523 0.281 + 98 -1.0116 3.8728 1.0344 0.8482 0.1138 0.2859 0.2182 0.0197 0.0000 -0.0054 0.0523 0.275 + 99 -1.2891 3.7630 1.1046 0.8452 0.1082 0.2933 0.2239 0.0198 0.0000 -0.0043 0.0526 0.269 + 100 -1.5912 3.6435 1.1542 0.8414 0.1019 0.3017 0.2302 0.0198 0.0000 -0.0034 0.0532 0.265 + 101 -1.9146 3.5155 1.1831 0.8366 0.0955 0.3109 0.2373 0.0199 0.0000 -0.0026 0.0541 0.261 + 102 -2.2558 3.3805 1.1921 0.8310 0.0899 0.3212 0.2452 0.0200 0.0000 -0.0019 0.0553 0.258 + 103 -2.6109 3.2400 1.1821 0.8250 0.0854 0.3328 0.2540 0.0203 0.0000 -0.0014 0.0567 0.255 + 104 -2.9762 3.0955 1.1548 0.8177 0.0821 0.3454 0.2636 0.0205 0.0000 -0.0008 0.0583 0.253 + 105 -3.3476 2.9485 1.1122 0.8088 0.0797 0.3588 0.2738 0.0206 0.0000 -0.0002 0.0600 0.251 + 106 -3.7210 2.8008 1.0564 0.7982 0.0781 0.3728 0.2846 0.0208 0.0000 0.0004 0.0618 0.248 + 107 -4.0924 2.6538 0.9900 0.7850 0.0771 0.3871 0.2955 0.0207 0.0000 0.0012 0.0636 0.246 + 108 -4.4577 2.5093 0.9155 0.7686 0.0767 0.4010 0.3060 0.0206 0.0000 0.0020 0.0651 0.243 + 109 -4.8128 2.3687 0.8353 0.7478 0.0770 0.4135 0.3156 0.0204 0.0000 0.0031 0.0663 0.240 + 110 -5.1540 2.2338 0.7518 0.7226 0.0778 0.4238 0.3234 0.0200 0.0000 0.0044 0.0669 0.236 + 111 -5.4774 2.1058 0.6671 0.6916 0.0793 0.4304 0.3285 0.0194 0.0000 0.0061 0.0666 0.232 + 112 -5.7795 1.9862 0.5830 0.6543 0.0814 0.4319 0.3296 0.0183 0.0000 0.0081 0.0651 0.225 + 113 -6.0570 1.8764 0.5012 0.6107 0.0840 0.4269 0.3258 0.0172 0.0000 0.0107 0.0621 0.217 + 114 -6.3069 1.7776 0.4225 0.5598 0.0868 0.4132 0.3153 0.0157 0.0000 0.0136 0.0574 0.207 + 115 -6.5264 1.6907 0.3478 0.5015 0.0897 0.3893 0.2971 0.0137 0.0000 0.0166 0.0509 0.194 + 116 -6.7314 1.6096 0.3326 0.4323 0.0926 0.3527 0.2692 0.0113 0.0000 0.0193 0.0425 0.178 + 117 -6.9144 1.5372 0.2507 0.3482 0.0953 0.2977 0.2272 0.0083 0.0000 0.0207 0.0322 0.159 + 118 -7.0535 1.4822 0.1746 0.2554 0.0975 0.2267 0.1730 0.0050 0.0000 0.0193 0.0215 0.139 + 119 -7.1471 1.4451 0.1029 0.1560 0.0990 0.1422 0.1085 0.0019 0.0000 0.0140 0.0119 0.121 120 -7.1941 1.4265 0.0340 0.0525 0.0998 0.0488 0.0372 -0.0012 0.0000 0.0052 0.0037 0.112 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,67 +198,67 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.382 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.390 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.401 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.409 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.412 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.411 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.404 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.391 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.368 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.325 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.288 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.279 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.270 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.262 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.255 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.248 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.219 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.392 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.398 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.404 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.420 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.422 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.413 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.409 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.383 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.362 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.323 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.281 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.271 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.269 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.261 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.247 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.209 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.193 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.179 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.161 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.136 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.116 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.099 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.194 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.180 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.159 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.139 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.105 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01069 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.06565 - CDsurf = -0.00022 Cnsurf = -0.00000 + CLsurf = 0.01062 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.06573 + CDsurf = -0.00022 Cnsurf = 0.00000 CDisurf = -0.00022 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01078 CDsurf = -0.00022 + CLsurf = 0.01071 CDsurf = -0.00022 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.2435 0.1819 0.1034 0.0096 -0.0032 0.0000 0.0046 0.0003 -0.231 - 152 -1.3090 31.2096 11.6724 0.3455 0.1957 0.0422 0.0113 -0.0010 0.0000 0.0058 0.0008 -0.262 - 153 -0.9350 34.0626 12.7394 0.3773 0.1801 0.0267 0.0112 -0.0001 0.0000 0.0070 0.0014 -0.374 - 154 -0.5610 36.1619 13.5246 0.3953 0.1751 0.0182 0.0109 0.0006 0.0000 0.0075 0.0021 -0.438 - 155 -0.1870 37.5332 14.0374 0.4059 0.1754 0.0124 0.0107 0.0017 0.0000 0.0077 0.0034 -0.467 - 156 0.1870 37.5332 14.0374 0.4059 0.1754 0.0124 0.0107 0.0017 0.0000 0.0077 0.0034 -0.467 - 157 0.5610 36.1619 13.5246 0.3953 0.1751 0.0182 0.0109 0.0006 0.0000 0.0075 0.0021 -0.438 - 158 0.9350 34.0626 12.7394 0.3773 0.1801 0.0267 0.0112 -0.0001 0.0000 0.0070 0.0014 -0.374 - 159 1.3090 31.2096 11.6724 0.3455 0.1957 0.0422 0.0113 -0.0010 0.0000 0.0058 0.0008 -0.262 - 160 1.6830 26.5957 9.9468 0.2435 0.1819 0.1034 0.0096 -0.0032 0.0000 0.0046 0.0003 -0.231 + 151 -1.6830 26.5957 9.9468 0.2417 0.1819 0.1027 0.0095 -0.0032 0.0000 0.0046 0.0003 -0.237 + 152 -1.3090 31.2096 11.6724 0.3430 0.1957 0.0419 0.0112 -0.0010 0.0000 0.0058 0.0008 -0.268 + 153 -0.9350 34.0626 12.7394 0.3748 0.1802 0.0266 0.0111 -0.0001 0.0000 0.0070 0.0014 -0.380 + 154 -0.5610 36.1619 13.5246 0.3928 0.1753 0.0181 0.0109 0.0006 0.0000 0.0075 0.0022 -0.444 + 155 -0.1870 37.5332 14.0374 0.4034 0.1756 0.0123 0.0106 0.0017 0.0000 0.0077 0.0034 -0.473 + 156 0.1870 37.5332 14.0374 0.4034 0.1756 0.0123 0.0106 0.0017 0.0000 0.0077 0.0034 -0.473 + 157 0.5610 36.1619 13.5246 0.3928 0.1753 0.0181 0.0109 0.0006 0.0000 0.0075 0.0022 -0.444 + 158 0.9350 34.0626 12.7394 0.3748 0.1802 0.0266 0.0111 -0.0001 0.0000 0.0070 0.0014 -0.380 + 159 1.3090 31.2096 11.6724 0.3430 0.1957 0.0419 0.0112 -0.0010 0.0000 0.0058 0.0008 -0.268 + 160 1.6830 26.5957 9.9468 0.2417 0.1819 0.1027 0.0095 -0.0032 0.0000 0.0046 0.0003 -0.237 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = 0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = 0.00000 CDsurf = 0.00000 Cnsurf = -0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0002 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.634 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.294 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.051 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.361 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.477 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.571 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.649 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.738 + 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.663 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.212 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.028 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.395 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.521 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.592 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.663 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.741 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_04_06.txt b/regression/scripts/AVL/avl_files/strip_forces_case_04_06.txt index 8b4f69dcc2..4e89561a34 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_04_06.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_04_06.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.52932 Clsurf = -0.10436 - CYsurf = -0.02497 Cmsurf = -0.48086 - CDsurf = 0.02414 Cnsurf = -0.01632 - CDisurf = 0.02414 CDvsurf = 0.00000 + CLsurf = 0.52978 Clsurf = -0.10439 + CYsurf = -0.02443 Cmsurf = -0.48104 + CDsurf = 0.02324 Cnsurf = -0.01640 + CDisurf = 0.02324 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.03411 CDsurf = 0.04713 + CLsurf = 1.03494 CDsurf = 0.04536 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 6.7406 0.2305 0.8862 0.6878 1.1031 0.0000 -0.0469 -0.2177 0.318 - 2 0.1025 7.6885 1.0492 5.9758 0.2303 0.9695 0.7525 0.2079 0.0000 -0.0468 -0.1988 0.312 - 3 0.2837 7.5620 1.7073 5.9130 0.2291 0.9884 0.7671 0.1522 0.0000 -0.0438 -0.1973 0.307 - 4 0.5530 7.3741 2.3052 5.8852 0.2260 1.0131 0.7863 0.1365 0.0000 -0.0389 -0.1968 0.300 - 5 0.9075 7.1267 2.8223 5.8454 0.2191 1.0454 0.8114 0.1216 0.0000 -0.0336 -0.1971 0.291 - 6 1.3432 6.8226 3.2414 5.7805 0.2021 1.0829 0.8405 0.1122 0.0000 -0.0286 -0.1986 0.284 - 7 1.8554 6.4651 3.5491 5.6954 0.1653 1.1293 0.8765 0.1020 0.0000 -0.0242 -0.2020 0.278 - 8 2.4386 6.0582 3.7368 5.5390 0.1292 1.1783 0.9145 0.0786 0.0000 -0.0219 -0.2071 0.274 - 9 3.0862 5.6062 3.8005 5.3580 0.1137 1.2351 0.9586 0.0672 0.0000 -0.0206 -0.2146 0.271 - 10 3.7613 5.1351 3.4440 5.1414 0.1013 1.2980 1.0073 0.0529 0.0000 -0.0209 -0.2242 0.271 - 11 4.4532 4.6522 3.3149 4.9039 0.0855 1.3713 1.0642 0.0346 0.0000 -0.0228 -0.2367 0.271 - 12 5.1831 4.1429 3.0930 4.6478 0.0601 1.4650 1.1370 0.0126 0.0000 -0.0242 -0.2519 0.271 - 13 6.0123 3.7903 3.4706 4.3558 0.0422 1.4340 1.1668 0.0009 0.0000 -0.0181 -0.2779 0.266 - 14 6.9353 3.6075 3.3775 4.1318 0.0384 1.4286 1.1625 0.0035 0.0000 -0.0180 -0.2769 0.265 - 15 7.8737 3.4215 3.2389 3.9252 0.0324 1.4311 1.1645 0.0027 0.0000 -0.0176 -0.2771 0.265 - 16 8.8172 3.2345 3.0619 3.7263 0.0285 1.4375 1.1697 0.0009 0.0000 -0.0172 -0.2778 0.265 - 17 9.7556 3.0486 2.8543 3.5278 0.0276 1.4443 1.1752 -0.0009 0.0000 -0.0168 -0.2786 0.264 - 18 10.6786 2.8657 2.6240 3.3311 0.0287 1.4512 1.1809 -0.0027 0.0000 -0.0163 -0.2794 0.264 - 19 11.5760 2.6879 2.3787 3.1347 0.0312 1.4564 1.1851 -0.0045 0.0000 -0.0156 -0.2796 0.263 - 20 12.4328 2.5181 2.1010 2.9388 0.0348 1.4579 1.1862 -0.0063 0.0000 -0.0146 -0.2789 0.262 - 21 13.2400 2.3582 1.8520 2.7420 0.0400 1.4528 1.1821 -0.0075 0.0000 -0.0131 -0.2766 0.261 - 22 13.9941 2.2087 1.6074 2.5408 0.0473 1.4375 1.1697 -0.0086 0.0000 -0.0107 -0.2717 0.259 - 23 14.6868 2.0715 1.3716 2.3295 0.0571 1.4054 1.1435 -0.0090 0.0000 -0.0069 -0.2625 0.256 - 24 15.3105 1.9479 1.1479 2.1005 0.0693 1.3476 1.0966 -0.0087 0.0000 -0.0017 -0.2473 0.252 - 25 15.8583 1.8393 0.9381 1.8421 0.0827 1.2512 1.0181 -0.0060 0.0000 0.0033 -0.2255 0.247 - 26 16.3244 1.7470 0.7427 1.5479 0.0963 1.1044 0.8986 0.0064 0.0000 -0.0000 -0.2020 0.250 - 27 16.6722 1.4928 0.4131 1.2298 0.1108 2.7667 0.8456 -0.0486 0.0000 -0.0043 -0.1077 0.255 - 28 16.9098 1.1466 0.2292 0.9081 0.1298 2.6934 0.8232 -0.1037 0.0000 0.0289 -0.0886 0.215 - 29 17.0696 0.9138 0.1104 0.5592 0.1444 2.1213 0.6483 -0.1474 0.0000 0.0586 -0.0521 0.160 - 30 17.1499 0.7967 0.0322 0.1890 0.1518 0.8549 0.2613 -0.1122 0.0000 0.0364 -0.0140 0.111 + 1 0.0114 7.7520 0.3539 6.7601 0.2305 0.8892 0.6901 1.1044 0.0000 -0.0486 -0.2196 0.320 + 2 0.1025 7.6885 1.0491 5.9918 0.2303 0.9722 0.7545 0.2081 0.0000 -0.0481 -0.2003 0.314 + 3 0.2837 7.5620 1.7073 5.9293 0.2294 0.9911 0.7692 0.1526 0.0000 -0.0451 -0.1989 0.309 + 4 0.5530 7.3741 2.3052 5.8975 0.2265 1.0163 0.7888 0.1317 0.0000 -0.0403 -0.1983 0.301 + 5 0.9075 7.1267 2.8223 5.8600 0.2197 1.0473 0.8128 0.1251 0.0000 -0.0350 -0.1986 0.293 + 6 1.3432 6.8226 3.2414 5.7929 0.2028 1.0862 0.8431 0.1081 0.0000 -0.0300 -0.2001 0.286 + 7 1.8554 6.4651 3.5491 5.6903 0.1659 1.1321 0.8786 0.0855 0.0000 -0.0260 -0.2033 0.280 + 8 2.4386 6.0582 3.7368 5.5539 0.1299 1.1820 0.9174 0.0766 0.0000 -0.0230 -0.2084 0.275 + 9 3.0862 5.6062 3.8005 5.3859 0.1146 1.2422 0.9641 0.0649 0.0000 -0.0210 -0.2159 0.272 + 10 3.7613 5.1351 3.4440 5.1076 0.1020 1.2902 1.0013 0.0491 0.0000 -0.0238 -0.2253 0.274 + 11 4.4532 4.6522 3.3149 4.9043 0.0854 1.3718 1.0646 0.0329 0.0000 -0.0229 -0.2368 0.271 + 12 5.1831 4.1429 3.0930 4.6441 0.0594 1.4642 1.1363 0.0110 0.0000 -0.0231 -0.2508 0.270 + 13 6.0123 3.7903 3.4706 4.3590 0.0417 1.4350 1.1676 0.0010 0.0000 -0.0166 -0.2768 0.264 + 14 6.9353 3.6075 3.3775 4.1340 0.0382 1.4294 1.1631 0.0034 0.0000 -0.0163 -0.2756 0.264 + 15 7.8737 3.4215 3.2389 3.9262 0.0322 1.4315 1.1648 0.0026 0.0000 -0.0160 -0.2757 0.264 + 16 8.8172 3.2345 3.0619 3.7276 0.0283 1.4380 1.1701 0.0010 0.0000 -0.0155 -0.2764 0.263 + 17 9.7556 3.0486 2.8543 3.5292 0.0275 1.4450 1.1757 -0.0010 0.0000 -0.0151 -0.2772 0.263 + 18 10.6786 2.8657 2.6239 3.3323 0.0286 1.4518 1.1813 -0.0027 0.0000 -0.0146 -0.2780 0.262 + 19 11.5760 2.6879 2.3787 3.1357 0.0311 1.4569 1.1854 -0.0046 0.0000 -0.0139 -0.2782 0.262 + 20 12.4328 2.5181 2.1010 2.9397 0.0348 1.4583 1.1866 -0.0063 0.0000 -0.0129 -0.2775 0.261 + 21 13.2400 2.3582 1.8520 2.7427 0.0400 1.4532 1.1824 -0.0077 0.0000 -0.0114 -0.2752 0.260 + 22 13.9941 2.2087 1.6074 2.5413 0.0473 1.4378 1.1699 -0.0087 0.0000 -0.0090 -0.2702 0.258 + 23 14.6868 2.0715 1.3716 2.3299 0.0571 1.4056 1.1438 -0.0091 0.0000 -0.0052 -0.2610 0.255 + 24 15.3105 1.9479 1.1479 2.1004 0.0693 1.3476 1.0966 -0.0088 0.0000 0.0000 -0.2458 0.250 + 25 15.8583 1.8393 0.9381 1.8423 0.0826 1.2513 1.0182 -0.0062 0.0000 0.0050 -0.2240 0.245 + 26 16.3244 1.7470 0.7427 1.5475 0.0960 1.1041 0.8984 0.0062 0.0000 0.0017 -0.2005 0.248 + 27 16.6722 1.4928 0.4131 1.2294 0.1105 2.7659 0.8453 -0.0489 0.0000 -0.0030 -0.1070 0.254 + 28 16.9098 1.1466 0.2292 0.9079 0.1298 2.6931 0.8231 -0.1041 0.0000 0.0300 -0.0881 0.214 + 29 17.0696 0.9138 0.1104 0.5592 0.1446 2.1215 0.6484 -0.1478 0.0000 0.0593 -0.0518 0.159 + 30 17.1499 0.7967 0.0322 0.1891 0.1525 0.8555 0.2615 -0.1128 0.0000 0.0366 -0.0140 0.110 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.52932 Clsurf = 0.10436 - CYsurf = 0.02497 Cmsurf = -0.48085 - CDsurf = 0.02414 Cnsurf = 0.01632 - CDisurf = 0.02414 CDvsurf = 0.00000 + CLsurf = 0.52978 Clsurf = 0.10439 + CYsurf = 0.02443 Cmsurf = -0.48103 + CDsurf = 0.02324 Cnsurf = 0.01640 + CDisurf = 0.02324 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.03410 CDsurf = 0.04713 + CLsurf = 1.03494 CDsurf = 0.04536 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 6.7406 0.2307 0.8862 0.6878 1.1032 0.0000 -0.0469 0.2177 0.318 - 32 -0.1025 7.6885 1.0492 5.9758 0.2303 0.9695 0.7525 0.2079 0.0000 -0.0468 0.1988 0.312 - 33 -0.2837 7.5620 1.7073 5.9130 0.2291 0.9884 0.7671 0.1522 0.0000 -0.0438 0.1973 0.307 - 34 -0.5530 7.3741 2.3052 5.8851 0.2260 1.0131 0.7863 0.1365 0.0000 -0.0389 0.1968 0.300 - 35 -0.9075 7.1267 2.8223 5.8454 0.2191 1.0454 0.8114 0.1216 0.0000 -0.0336 0.1970 0.291 - 36 -1.3432 6.8226 3.2414 5.7805 0.2021 1.0829 0.8405 0.1122 0.0000 -0.0286 0.1986 0.284 - 37 -1.8554 6.4651 3.5491 5.6954 0.1653 1.1293 0.8765 0.1020 0.0000 -0.0242 0.2020 0.278 - 38 -2.4386 6.0582 3.7368 5.5390 0.1292 1.1783 0.9145 0.0786 0.0000 -0.0219 0.2071 0.274 - 39 -3.0862 5.6062 3.8005 5.3579 0.1137 1.2351 0.9586 0.0672 0.0000 -0.0206 0.2146 0.271 - 40 -3.7613 5.1351 3.4440 5.1414 0.1013 1.2980 1.0073 0.0529 0.0000 -0.0209 0.2242 0.271 - 41 -4.4532 4.6522 3.3149 4.9039 0.0855 1.3713 1.0642 0.0346 0.0000 -0.0228 0.2367 0.271 - 42 -5.1831 4.1429 3.0930 4.6478 0.0601 1.4650 1.1370 0.0126 0.0000 -0.0242 0.2519 0.271 - 43 -6.0123 3.7903 3.4706 4.3557 0.0422 1.4340 1.1668 0.0009 0.0000 -0.0181 0.2779 0.266 - 44 -6.9353 3.6075 3.3775 4.1318 0.0384 1.4286 1.1625 0.0035 0.0000 -0.0180 0.2769 0.265 - 45 -7.8737 3.4215 3.2389 3.9252 0.0324 1.4311 1.1645 0.0027 0.0000 -0.0176 0.2771 0.265 - 46 -8.8172 3.2345 3.0619 3.7263 0.0285 1.4375 1.1697 0.0009 0.0000 -0.0172 0.2778 0.265 - 47 -9.7556 3.0486 2.8543 3.5277 0.0276 1.4443 1.1752 -0.0009 0.0000 -0.0168 0.2786 0.264 - 48 -10.6786 2.8657 2.6240 3.3311 0.0287 1.4512 1.1808 -0.0027 0.0000 -0.0163 0.2794 0.264 - 49 -11.5760 2.6879 2.3787 3.1347 0.0312 1.4564 1.1851 -0.0045 0.0000 -0.0156 0.2796 0.263 - 50 -12.4328 2.5181 2.1010 2.9388 0.0348 1.4579 1.1862 -0.0063 0.0000 -0.0146 0.2789 0.262 - 51 -13.2400 2.3582 1.8520 2.7420 0.0400 1.4528 1.1821 -0.0075 0.0000 -0.0131 0.2766 0.261 - 52 -13.9941 2.2087 1.6074 2.5408 0.0473 1.4375 1.1697 -0.0086 0.0000 -0.0107 0.2717 0.259 - 53 -14.6868 2.0715 1.3716 2.3294 0.0571 1.4054 1.1435 -0.0090 0.0000 -0.0069 0.2625 0.256 - 54 -15.3105 1.9479 1.1479 2.1004 0.0693 1.3476 1.0965 -0.0087 0.0000 -0.0017 0.2473 0.252 - 55 -15.8583 1.8393 0.9381 1.8421 0.0827 1.2512 1.0181 -0.0060 0.0000 0.0033 0.2254 0.247 - 56 -16.3244 1.7470 0.7427 1.5479 0.0963 1.1044 0.8986 0.0064 0.0000 -0.0000 0.2020 0.250 - 57 -16.6722 1.4928 0.4131 1.2298 0.1108 2.7667 0.8455 -0.0486 0.0000 -0.0043 0.1077 0.255 - 58 -16.9098 1.1466 0.2292 0.9081 0.1298 2.6934 0.8232 -0.1037 0.0000 0.0289 0.0886 0.215 - 59 -17.0696 0.9138 0.1104 0.5592 0.1444 2.1212 0.6483 -0.1474 0.0000 0.0586 0.0521 0.160 - 60 -17.1499 0.7967 0.0322 0.1890 0.1518 0.8549 0.2613 -0.1122 0.0000 0.0364 0.0140 0.111 + 31 -0.0114 7.7520 0.3539 6.7601 0.2305 0.8892 0.6901 1.1044 0.0000 -0.0486 0.2196 0.320 + 32 -0.1025 7.6885 1.0491 5.9918 0.2303 0.9722 0.7545 0.2081 0.0000 -0.0481 0.2003 0.314 + 33 -0.2837 7.5620 1.7073 5.9293 0.2294 0.9911 0.7692 0.1526 0.0000 -0.0451 0.1989 0.309 + 34 -0.5530 7.3741 2.3052 5.8975 0.2265 1.0163 0.7888 0.1317 0.0000 -0.0403 0.1983 0.301 + 35 -0.9075 7.1267 2.8223 5.8600 0.2197 1.0473 0.8128 0.1251 0.0000 -0.0350 0.1986 0.293 + 36 -1.3432 6.8226 3.2414 5.7929 0.2028 1.0862 0.8431 0.1081 0.0000 -0.0300 0.2001 0.286 + 37 -1.8554 6.4651 3.5491 5.6903 0.1659 1.1321 0.8786 0.0855 0.0000 -0.0260 0.2033 0.280 + 38 -2.4386 6.0582 3.7368 5.5539 0.1299 1.1820 0.9174 0.0766 0.0000 -0.0230 0.2084 0.275 + 39 -3.0862 5.6062 3.8005 5.3859 0.1146 1.2422 0.9641 0.0649 0.0000 -0.0210 0.2159 0.272 + 40 -3.7613 5.1351 3.4440 5.1076 0.1020 1.2902 1.0013 0.0491 0.0000 -0.0238 0.2253 0.274 + 41 -4.4532 4.6522 3.3149 4.9043 0.0854 1.3718 1.0646 0.0329 0.0000 -0.0229 0.2368 0.271 + 42 -5.1831 4.1429 3.0930 4.6441 0.0594 1.4642 1.1363 0.0110 0.0000 -0.0231 0.2508 0.270 + 43 -6.0123 3.7903 3.4706 4.3590 0.0417 1.4350 1.1676 0.0010 0.0000 -0.0166 0.2768 0.264 + 44 -6.9353 3.6075 3.3775 4.1340 0.0382 1.4294 1.1631 0.0034 0.0000 -0.0163 0.2756 0.264 + 45 -7.8737 3.4215 3.2389 3.9262 0.0322 1.4315 1.1648 0.0026 0.0000 -0.0160 0.2757 0.264 + 46 -8.8172 3.2345 3.0619 3.7276 0.0283 1.4380 1.1701 0.0010 0.0000 -0.0155 0.2764 0.263 + 47 -9.7556 3.0486 2.8543 3.5292 0.0275 1.4449 1.1757 -0.0010 0.0000 -0.0151 0.2772 0.263 + 48 -10.6786 2.8657 2.6239 3.3322 0.0286 1.4518 1.1813 -0.0027 0.0000 -0.0146 0.2780 0.262 + 49 -11.5760 2.6879 2.3787 3.1356 0.0311 1.4569 1.1854 -0.0046 0.0000 -0.0139 0.2782 0.262 + 50 -12.4328 2.5181 2.1010 2.9397 0.0348 1.4583 1.1866 -0.0063 0.0000 -0.0129 0.2775 0.261 + 51 -13.2400 2.3582 1.8520 2.7427 0.0400 1.4532 1.1824 -0.0077 0.0000 -0.0114 0.2752 0.260 + 52 -13.9941 2.2087 1.6074 2.5413 0.0473 1.4378 1.1699 -0.0087 0.0000 -0.0090 0.2702 0.258 + 53 -14.6868 2.0715 1.3716 2.3299 0.0571 1.4056 1.1438 -0.0091 0.0000 -0.0052 0.2610 0.255 + 54 -15.3105 1.9479 1.1479 2.1004 0.0693 1.3476 1.0965 -0.0088 0.0000 0.0000 0.2458 0.250 + 55 -15.8583 1.8393 0.9381 1.8423 0.0826 1.2513 1.0182 -0.0062 0.0000 0.0050 0.2240 0.245 + 56 -16.3244 1.7470 0.7427 1.5475 0.0960 1.1041 0.8984 0.0062 0.0000 0.0017 0.2005 0.248 + 57 -16.6722 1.4928 0.4131 1.2294 0.1105 2.7659 0.8453 -0.0489 0.0000 -0.0030 0.1070 0.254 + 58 -16.9098 1.1466 0.2292 0.9079 0.1298 2.6931 0.8231 -0.1041 0.0000 0.0300 0.0881 0.214 + 59 -17.0696 0.9138 0.1104 0.5592 0.1446 2.1215 0.6484 -0.1478 0.0000 0.0593 0.0518 0.159 + 60 -17.1499 0.7967 0.0322 0.1891 0.1525 0.8555 0.2615 -0.1128 0.0000 0.0366 0.0140 0.110 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06607 Clsurf = -0.00681 - CYsurf = -0.01054 Cmsurf = -0.32432 - CDsurf = 0.00695 Cnsurf = 0.00559 - CDisurf = 0.00695 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06591 Clsurf = -0.00679 + CYsurf = -0.01052 Cmsurf = -0.32357 + CDsurf = 0.00694 Cnsurf = 0.00558 + CDisurf = 0.00694 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.40268 CDsurf = 0.04182 + CLsurf = 0.40173 CDsurf = 0.04174 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.7447 0.1726 0.4788 0.3639 0.2873 0.0000 -0.0191 -0.1054 0.303 - 62 0.0418 4.2566 0.2392 1.4022 0.1734 0.4250 0.3231 0.0644 0.0000 -0.0186 -0.0883 0.308 - 63 0.1156 4.2274 0.3930 1.3771 0.1736 0.4235 0.3220 0.0497 0.0000 -0.0177 -0.0868 0.305 - 64 0.2254 4.1839 0.5386 1.3696 0.1731 0.4264 0.3241 0.0465 0.0000 -0.0159 -0.0857 0.299 - 65 0.3698 4.1268 0.6730 1.3673 0.1716 0.4320 0.3284 0.0452 0.0000 -0.0138 -0.0848 0.292 - 66 0.5474 4.0565 0.7936 1.3653 0.1687 0.4392 0.3339 0.0443 0.0000 -0.0115 -0.0841 0.284 - 67 0.7617 3.9717 0.9441 1.3603 0.1642 0.4474 0.3401 0.0434 0.0000 -0.0093 -0.0836 0.277 - 68 1.0116 3.8728 1.0344 1.3558 0.1578 0.4577 0.3479 0.0428 0.0000 -0.0073 -0.0836 0.271 - 69 1.2891 3.7630 1.1046 1.3482 0.1497 0.4686 0.3562 0.0427 0.0000 -0.0055 -0.0839 0.265 - 70 1.5912 3.6435 1.1542 1.3397 0.1405 0.4813 0.3658 0.0423 0.0000 -0.0040 -0.0848 0.261 - 71 1.9146 3.5155 1.1831 1.3290 0.1313 0.4951 0.3763 0.0424 0.0000 -0.0027 -0.0860 0.257 - 72 2.2558 3.3805 1.1921 1.3151 0.1232 0.5098 0.3875 0.0422 0.0000 -0.0017 -0.0876 0.254 - 73 2.6109 3.2400 1.1821 1.3002 0.1169 0.5262 0.4000 0.0424 0.0000 -0.0008 -0.0895 0.252 - 74 2.9762 3.0955 1.1548 1.2831 0.1123 0.5437 0.4133 0.0427 0.0000 0.0001 -0.0917 0.250 - 75 3.3476 2.9485 1.1122 1.2632 0.1092 0.5624 0.4275 0.0423 0.0000 0.0010 -0.0940 0.248 - 76 3.7210 2.8008 1.0564 1.2408 0.1073 0.5819 0.4423 0.0426 0.0000 0.0020 -0.0964 0.246 - 77 4.0924 2.6538 0.9900 1.2133 0.1062 0.6008 0.4567 0.0423 0.0000 0.0030 -0.0987 0.243 - 78 4.4577 2.5093 0.9155 1.1817 0.1060 0.6193 0.4707 0.0421 0.0000 0.0043 -0.1007 0.241 - 79 4.8128 2.3687 0.8353 1.1432 0.1067 0.6351 0.4827 0.0413 0.0000 0.0058 -0.1020 0.238 - 80 5.1540 2.2338 0.7518 1.0992 0.1082 0.6479 0.4925 0.0404 0.0000 0.0077 -0.1025 0.234 - 81 5.4774 2.1058 0.6671 1.0480 0.1106 0.6557 0.4984 0.0391 0.0000 0.0101 -0.1018 0.230 - 82 5.7795 1.9862 0.5830 0.9870 0.1139 0.6552 0.4980 0.0367 0.0000 0.0131 -0.0991 0.224 - 83 6.0570 1.8764 0.5012 0.9185 0.1178 0.6459 0.4909 0.0342 0.0000 0.0168 -0.0944 0.216 - 84 6.3069 1.7776 0.4225 0.8388 0.1221 0.6231 0.4736 0.0311 0.0000 0.0210 -0.0870 0.206 - 85 6.5264 1.6907 0.3478 0.7497 0.1264 0.5861 0.4455 0.0269 0.0000 0.0254 -0.0771 0.193 - 86 6.7314 1.6096 0.3326 0.6453 0.1308 0.5304 0.4031 0.0223 0.0000 0.0293 -0.0644 0.177 - 87 6.9144 1.5372 0.2507 0.5189 0.1349 0.4473 0.3399 0.0161 0.0000 0.0312 -0.0488 0.158 - 88 7.0535 1.4822 0.1746 0.3799 0.1381 0.3403 0.2586 0.0093 0.0000 0.0290 -0.0327 0.138 - 89 7.1471 1.4451 0.1029 0.2319 0.1404 0.2136 0.1624 0.0032 0.0000 0.0210 -0.0181 0.121 - 90 7.1941 1.4265 0.0340 0.0781 0.1416 0.0738 0.0561 -0.0028 0.0000 0.0077 -0.0057 0.112 + 61 0.0047 4.2713 0.0803 1.7381 0.1728 0.4770 0.3626 0.2856 0.0000 -0.0191 -0.1050 0.303 + 62 0.0418 4.2566 0.2392 1.3976 0.1734 0.4236 0.3220 0.0642 0.0000 -0.0186 -0.0881 0.308 + 63 0.1156 4.2274 0.3930 1.3726 0.1737 0.4221 0.3209 0.0496 0.0000 -0.0176 -0.0865 0.305 + 64 0.2254 4.1839 0.5386 1.3650 0.1732 0.4251 0.3231 0.0461 0.0000 -0.0159 -0.0855 0.299 + 65 0.3698 4.1268 0.6730 1.3631 0.1717 0.4307 0.3274 0.0450 0.0000 -0.0138 -0.0846 0.292 + 66 0.5474 4.0565 0.7936 1.3600 0.1688 0.4375 0.3325 0.0443 0.0000 -0.0115 -0.0838 0.285 + 67 0.7617 3.9717 0.9441 1.3570 0.1643 0.4463 0.3392 0.0435 0.0000 -0.0093 -0.0834 0.278 + 68 1.0116 3.8728 1.0344 1.3503 0.1580 0.4558 0.3465 0.0426 0.0000 -0.0073 -0.0832 0.271 + 69 1.2891 3.7630 1.1046 1.3437 0.1499 0.4671 0.3551 0.0424 0.0000 -0.0055 -0.0837 0.266 + 70 1.5912 3.6435 1.1542 1.3353 0.1407 0.4797 0.3646 0.0422 0.0000 -0.0040 -0.0845 0.261 + 71 1.9146 3.5155 1.1831 1.3243 0.1314 0.4933 0.3750 0.0422 0.0000 -0.0028 -0.0857 0.257 + 72 2.2558 3.3805 1.1921 1.3113 0.1233 0.5083 0.3864 0.0422 0.0000 -0.0017 -0.0873 0.254 + 73 2.6109 3.2400 1.1821 1.2973 0.1170 0.5250 0.3990 0.0424 0.0000 -0.0008 -0.0893 0.252 + 74 2.9762 3.0955 1.1548 1.2805 0.1124 0.5426 0.4125 0.0426 0.0000 0.0001 -0.0915 0.250 + 75 3.3476 2.9485 1.1122 1.2604 0.1093 0.5611 0.4265 0.0426 0.0000 0.0010 -0.0939 0.248 + 76 3.7210 2.8008 1.0564 1.2375 0.1074 0.5802 0.4410 0.0427 0.0000 0.0019 -0.0962 0.246 + 77 4.0924 2.6538 0.9900 1.2107 0.1063 0.5995 0.4557 0.0423 0.0000 0.0030 -0.0985 0.243 + 78 4.4577 2.5093 0.9155 1.1793 0.1061 0.6181 0.4698 0.0418 0.0000 0.0042 -0.1005 0.241 + 79 4.8128 2.3687 0.8353 1.1416 0.1068 0.6342 0.4820 0.0413 0.0000 0.0058 -0.1019 0.238 + 80 5.1540 2.2338 0.7518 1.0979 0.1083 0.6472 0.4919 0.0404 0.0000 0.0077 -0.1024 0.234 + 81 5.4774 2.1058 0.6671 1.0462 0.1107 0.6546 0.4976 0.0390 0.0000 0.0101 -0.1016 0.230 + 82 5.7795 1.9862 0.5830 0.9859 0.1139 0.6545 0.4975 0.0366 0.0000 0.0131 -0.0990 0.224 + 83 6.0570 1.8764 0.5012 0.9173 0.1178 0.6450 0.4903 0.0343 0.0000 0.0168 -0.0943 0.216 + 84 6.3069 1.7776 0.4225 0.8385 0.1221 0.6229 0.4734 0.0311 0.0000 0.0210 -0.0870 0.206 + 85 6.5264 1.6907 0.3478 0.7495 0.1265 0.5858 0.4453 0.0270 0.0000 0.0254 -0.0771 0.193 + 86 6.7314 1.6096 0.3326 0.6448 0.1308 0.5300 0.4028 0.0222 0.0000 0.0293 -0.0644 0.177 + 87 6.9144 1.5372 0.2507 0.5185 0.1349 0.4469 0.3396 0.0160 0.0000 0.0312 -0.0487 0.158 + 88 7.0535 1.4822 0.1746 0.3799 0.1382 0.3402 0.2586 0.0093 0.0000 0.0290 -0.0327 0.138 + 89 7.1471 1.4451 0.1029 0.2317 0.1404 0.2135 0.1622 0.0032 0.0000 0.0210 -0.0181 0.121 + 90 7.1941 1.4265 0.0340 0.0780 0.1416 0.0737 0.0560 -0.0028 0.0000 0.0077 -0.0057 0.112 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06607 Clsurf = 0.00681 - CYsurf = 0.01054 Cmsurf = -0.32431 - CDsurf = 0.00695 Cnsurf = -0.00559 - CDisurf = 0.00695 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06591 Clsurf = 0.00679 + CYsurf = 0.01052 Cmsurf = -0.32357 + CDsurf = 0.00694 Cnsurf = -0.00558 + CDisurf = 0.00694 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.40268 CDsurf = 0.04181 + CLsurf = 0.40173 CDsurf = 0.04174 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.7447 0.1727 0.4788 0.3639 0.2873 0.0000 -0.0191 0.1054 0.303 - 92 -0.0418 4.2566 0.2392 1.4022 0.1734 0.4250 0.3231 0.0644 0.0000 -0.0186 0.0883 0.308 - 93 -0.1156 4.2274 0.3930 1.3771 0.1736 0.4235 0.3220 0.0497 0.0000 -0.0177 0.0868 0.305 - 94 -0.2254 4.1839 0.5386 1.3696 0.1731 0.4264 0.3241 0.0465 0.0000 -0.0159 0.0857 0.299 - 95 -0.3698 4.1268 0.6730 1.3673 0.1716 0.4320 0.3284 0.0452 0.0000 -0.0138 0.0848 0.292 - 96 -0.5474 4.0565 0.7936 1.3653 0.1687 0.4392 0.3339 0.0443 0.0000 -0.0115 0.0841 0.284 - 97 -0.7617 3.9717 0.9441 1.3603 0.1642 0.4474 0.3401 0.0434 0.0000 -0.0093 0.0836 0.277 - 98 -1.0116 3.8728 1.0344 1.3558 0.1578 0.4577 0.3479 0.0428 0.0000 -0.0073 0.0836 0.271 - 99 -1.2891 3.7630 1.1046 1.3482 0.1497 0.4686 0.3562 0.0427 0.0000 -0.0055 0.0839 0.265 - 100 -1.5912 3.6435 1.1542 1.3397 0.1405 0.4813 0.3658 0.0423 0.0000 -0.0040 0.0848 0.261 - 101 -1.9146 3.5155 1.1831 1.3290 0.1313 0.4951 0.3763 0.0424 0.0000 -0.0027 0.0860 0.257 - 102 -2.2558 3.3805 1.1921 1.3151 0.1232 0.5098 0.3875 0.0422 0.0000 -0.0017 0.0876 0.254 - 103 -2.6109 3.2400 1.1821 1.3002 0.1169 0.5262 0.3999 0.0424 0.0000 -0.0008 0.0895 0.252 - 104 -2.9762 3.0955 1.1548 1.2830 0.1123 0.5437 0.4133 0.0427 0.0000 0.0001 0.0917 0.250 - 105 -3.3476 2.9485 1.1122 1.2632 0.1092 0.5624 0.4275 0.0423 0.0000 0.0010 0.0940 0.248 - 106 -3.7210 2.8008 1.0564 1.2408 0.1073 0.5819 0.4423 0.0426 0.0000 0.0020 0.0964 0.246 - 107 -4.0924 2.6538 0.9900 1.2133 0.1062 0.6008 0.4567 0.0423 0.0000 0.0030 0.0987 0.243 - 108 -4.4577 2.5093 0.9155 1.1817 0.1060 0.6192 0.4707 0.0421 0.0000 0.0043 0.1007 0.241 - 109 -4.8128 2.3687 0.8353 1.1432 0.1067 0.6351 0.4827 0.0413 0.0000 0.0058 0.1020 0.238 - 110 -5.1540 2.2338 0.7518 1.0991 0.1082 0.6479 0.4924 0.0404 0.0000 0.0077 0.1025 0.234 - 111 -5.4774 2.1058 0.6671 1.0479 0.1106 0.6557 0.4984 0.0391 0.0000 0.0101 0.1018 0.230 - 112 -5.7795 1.9862 0.5830 0.9869 0.1138 0.6552 0.4980 0.0367 0.0000 0.0131 0.0991 0.224 - 113 -6.0570 1.8764 0.5012 0.9185 0.1178 0.6459 0.4909 0.0342 0.0000 0.0168 0.0944 0.216 - 114 -6.3069 1.7776 0.4225 0.8388 0.1221 0.6231 0.4736 0.0311 0.0000 0.0210 0.0870 0.206 - 115 -6.5264 1.6907 0.3478 0.7497 0.1264 0.5860 0.4454 0.0269 0.0000 0.0254 0.0771 0.193 - 116 -6.7314 1.6096 0.3326 0.6453 0.1308 0.5304 0.4031 0.0223 0.0000 0.0293 0.0644 0.177 - 117 -6.9144 1.5372 0.2507 0.5189 0.1349 0.4473 0.3399 0.0161 0.0000 0.0312 0.0488 0.158 - 118 -7.0535 1.4822 0.1746 0.3799 0.1381 0.3403 0.2586 0.0093 0.0000 0.0290 0.0327 0.138 - 119 -7.1471 1.4451 0.1029 0.2319 0.1404 0.2136 0.1624 0.0032 0.0000 0.0210 0.0181 0.121 - 120 -7.1941 1.4265 0.0340 0.0781 0.1416 0.0738 0.0561 -0.0028 0.0000 0.0077 0.0057 0.112 + 91 -0.0047 4.2713 0.0803 1.7381 0.1728 0.4770 0.3626 0.2856 0.0000 -0.0191 0.1050 0.303 + 92 -0.0418 4.2566 0.2392 1.3976 0.1734 0.4236 0.3220 0.0642 0.0000 -0.0186 0.0881 0.308 + 93 -0.1156 4.2274 0.3930 1.3726 0.1737 0.4221 0.3209 0.0496 0.0000 -0.0176 0.0865 0.305 + 94 -0.2254 4.1839 0.5386 1.3650 0.1732 0.4251 0.3231 0.0461 0.0000 -0.0159 0.0855 0.299 + 95 -0.3698 4.1268 0.6730 1.3631 0.1717 0.4307 0.3274 0.0450 0.0000 -0.0138 0.0846 0.292 + 96 -0.5474 4.0565 0.7936 1.3600 0.1688 0.4375 0.3325 0.0443 0.0000 -0.0115 0.0838 0.285 + 97 -0.7617 3.9717 0.9441 1.3570 0.1643 0.4463 0.3392 0.0435 0.0000 -0.0093 0.0834 0.278 + 98 -1.0116 3.8728 1.0344 1.3503 0.1580 0.4558 0.3465 0.0426 0.0000 -0.0073 0.0832 0.271 + 99 -1.2891 3.7630 1.1046 1.3437 0.1499 0.4671 0.3551 0.0424 0.0000 -0.0055 0.0837 0.266 + 100 -1.5912 3.6435 1.1542 1.3353 0.1407 0.4797 0.3646 0.0422 0.0000 -0.0040 0.0845 0.261 + 101 -1.9146 3.5155 1.1831 1.3243 0.1314 0.4933 0.3750 0.0422 0.0000 -0.0028 0.0857 0.257 + 102 -2.2558 3.3805 1.1921 1.3113 0.1233 0.5083 0.3864 0.0422 0.0000 -0.0017 0.0873 0.254 + 103 -2.6109 3.2400 1.1821 1.2973 0.1170 0.5250 0.3990 0.0424 0.0000 -0.0008 0.0893 0.252 + 104 -2.9762 3.0955 1.1548 1.2805 0.1124 0.5426 0.4125 0.0426 0.0000 0.0001 0.0915 0.250 + 105 -3.3476 2.9485 1.1122 1.2604 0.1093 0.5611 0.4265 0.0426 0.0000 0.0010 0.0939 0.248 + 106 -3.7210 2.8008 1.0564 1.2375 0.1074 0.5802 0.4410 0.0427 0.0000 0.0019 0.0962 0.246 + 107 -4.0924 2.6538 0.9900 1.2107 0.1063 0.5995 0.4557 0.0423 0.0000 0.0030 0.0985 0.243 + 108 -4.4577 2.5093 0.9155 1.1793 0.1061 0.6181 0.4698 0.0418 0.0000 0.0042 0.1005 0.241 + 109 -4.8128 2.3687 0.8353 1.1416 0.1068 0.6342 0.4820 0.0413 0.0000 0.0058 0.1019 0.238 + 110 -5.1540 2.2338 0.7518 1.0979 0.1083 0.6472 0.4919 0.0404 0.0000 0.0077 0.1024 0.234 + 111 -5.4774 2.1058 0.6671 1.0462 0.1107 0.6546 0.4976 0.0390 0.0000 0.0101 0.1016 0.230 + 112 -5.7795 1.9862 0.5830 0.9859 0.1139 0.6545 0.4975 0.0366 0.0000 0.0131 0.0990 0.224 + 113 -6.0570 1.8764 0.5012 0.9173 0.1178 0.6450 0.4903 0.0343 0.0000 0.0168 0.0943 0.216 + 114 -6.3069 1.7776 0.4225 0.8385 0.1221 0.6229 0.4734 0.0311 0.0000 0.0210 0.0870 0.206 + 115 -6.5264 1.6907 0.3478 0.7495 0.1265 0.5858 0.4453 0.0270 0.0000 0.0254 0.0771 0.193 + 116 -6.7314 1.6096 0.3326 0.6448 0.1308 0.5300 0.4028 0.0222 0.0000 0.0293 0.0644 0.177 + 117 -6.9144 1.5372 0.2507 0.5185 0.1349 0.4469 0.3396 0.0160 0.0000 0.0312 0.0487 0.158 + 118 -7.0535 1.4822 0.1746 0.3799 0.1382 0.3402 0.2586 0.0093 0.0000 0.0290 0.0327 0.138 + 119 -7.1471 1.4451 0.1029 0.2317 0.1404 0.2135 0.1622 0.0032 0.0000 0.0210 0.0181 0.121 + 120 -7.1941 1.4265 0.0340 0.0780 0.1416 0.0737 0.0560 -0.0028 0.0000 0.0077 0.0057 0.112 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,67 +198,67 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.398 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.408 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.419 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.428 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.431 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.408 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.414 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.421 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.437 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.439 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.430 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.421 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.405 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.378 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.332 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.292 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.281 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.270 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.261 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.253 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.245 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.212 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.424 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.396 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.372 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.329 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.285 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.273 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.269 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.260 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.202 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.187 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.172 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.153 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.128 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.108 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.092 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.152 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.131 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.112 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.097 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01720 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.09430 - CDsurf = -0.00015 Cnsurf = -0.00000 - CDisurf = -0.00015 CDvsurf = 0.00000 + CLsurf = 0.01713 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = 0.09438 + CDsurf = -0.00016 Cnsurf = -0.00000 + CDisurf = -0.00016 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01735 CDsurf = -0.00015 + CLsurf = 0.01728 CDsurf = -0.00016 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.3990 0.2621 0.1514 0.0162 -0.0056 0.0000 0.0061 0.0003 -0.129 - 152 -1.3090 31.2096 11.6724 0.5560 0.2791 0.0659 0.0184 -0.0016 0.0000 0.0079 0.0009 -0.181 - 153 -0.9350 34.0626 12.7394 0.6008 0.2504 0.0420 0.0179 -0.0000 0.0000 0.0098 0.0018 -0.297 - 154 -0.5610 36.1619 13.5246 0.6263 0.2398 0.0286 0.0174 0.0012 0.0000 0.0107 0.0028 -0.365 - 155 -0.1870 37.5332 14.0374 0.6420 0.2387 0.0194 0.0168 0.0035 0.0000 0.0109 0.0046 -0.400 - 156 0.1870 37.5332 14.0374 0.6420 0.2387 0.0194 0.0168 0.0035 0.0000 0.0109 0.0046 -0.400 - 157 0.5610 36.1619 13.5246 0.6263 0.2398 0.0286 0.0174 0.0012 0.0000 0.0107 0.0028 -0.365 - 158 0.9350 34.0626 12.7394 0.6008 0.2504 0.0420 0.0179 -0.0000 0.0000 0.0098 0.0018 -0.297 - 159 1.3090 31.2096 11.6724 0.5560 0.2791 0.0659 0.0184 -0.0016 0.0000 0.0079 0.0009 -0.181 - 160 1.6830 26.5957 9.9468 0.3990 0.2621 0.1514 0.0162 -0.0056 0.0000 0.0061 0.0003 -0.129 + 151 -1.6830 26.5957 9.9468 0.3972 0.2620 0.1508 0.0161 -0.0056 0.0000 0.0062 0.0003 -0.132 + 152 -1.3090 31.2096 11.6724 0.5536 0.2791 0.0656 0.0183 -0.0016 0.0000 0.0079 0.0009 -0.184 + 153 -0.9350 34.0626 12.7394 0.5983 0.2506 0.0418 0.0178 -0.0001 0.0000 0.0098 0.0018 -0.300 + 154 -0.5610 36.1619 13.5246 0.6237 0.2401 0.0285 0.0173 0.0012 0.0000 0.0107 0.0029 -0.368 + 155 -0.1870 37.5332 14.0374 0.6395 0.2390 0.0193 0.0167 0.0035 0.0000 0.0109 0.0046 -0.403 + 156 0.1870 37.5332 14.0374 0.6395 0.2390 0.0193 0.0167 0.0035 0.0000 0.0109 0.0046 -0.403 + 157 0.5610 36.1619 13.5246 0.6237 0.2401 0.0285 0.0173 0.0012 0.0000 0.0107 0.0029 -0.368 + 158 0.9350 34.0626 12.7394 0.5983 0.2506 0.0418 0.0178 -0.0001 0.0000 0.0098 0.0018 -0.300 + 159 1.3090 31.2096 11.6724 0.5536 0.2791 0.0656 0.0183 -0.0016 0.0000 0.0079 0.0009 -0.184 + 160 1.6830 26.5957 9.9468 0.3972 0.2620 0.1508 0.0161 -0.0056 0.0000 0.0062 0.0003 -0.132 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 + CLsurf = 0.00000 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = 0.00000 Cnsurf = -0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.823 - 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0003 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.438 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.324 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.487 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.602 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.692 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.784 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 1.809 + 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.963 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.382 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.370 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.535 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.625 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.705 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.787 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_05_01.txt b/regression/scripts/AVL/avl_files/strip_forces_case_05_01.txt index 471932866b..f2d378f3d8 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_05_01.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_05_01.txt @@ -7,188 +7,188 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.01064 Clsurf = 0.00256 - CYsurf = 0.00003 Cmsurf = 0.00227 - CDsurf = 0.00044 Cnsurf = -0.00019 + CLsurf = 0.01138 Clsurf = 0.00249 + CYsurf = -0.00000 Cmsurf = 0.00187 + CDsurf = 0.00044 Cnsurf = -0.00018 CDisurf = 0.00044 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.02071 CDsurf = 0.00085 + CLsurf = 0.02217 CDsurf = 0.00086 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 0.7719 0.0129 0.1292 0.1004 0.0230 0.0000 -0.0053 -0.0245 0.302 - 2 0.1025 7.6885 1.0492 0.7565 0.0120 0.1269 0.0986 0.0052 0.0000 -0.0053 -0.0243 0.304 - 3 0.2837 7.5620 1.7073 0.7516 0.0103 0.1282 0.0996 0.0040 0.0000 -0.0050 -0.0243 0.300 - 4 0.5530 7.3741 2.3052 0.7408 0.0078 0.1295 0.1006 0.0034 0.0000 -0.0046 -0.0242 0.296 - 5 0.9075 7.1267 2.8223 0.7192 0.0051 0.1301 0.1011 0.0029 0.0000 -0.0044 -0.0240 0.293 - 6 1.3432 6.8226 3.2414 0.6828 0.0055 0.1289 0.1002 0.0022 0.0000 -0.0043 -0.0239 0.293 - 7 1.8554 6.4651 3.5491 0.6282 0.0152 0.1252 0.0973 0.0016 0.0000 -0.0047 -0.0236 0.298 - 8 2.4386 6.0582 3.7368 0.5533 0.0227 0.1176 0.0914 0.0008 0.0000 -0.0056 -0.0231 0.311 - 9 3.0862 5.6062 3.8005 0.4585 0.0153 0.1053 0.0818 0.0002 0.0000 -0.0072 -0.0225 0.338 - 10 3.7613 5.1351 3.4440 0.3532 0.0055 0.0886 0.0688 -0.0002 0.0000 -0.0098 -0.0219 0.392 - 11 4.4532 4.6522 3.3149 0.2443 -0.0029 0.0676 0.0525 -0.0004 0.0000 -0.0135 -0.0217 0.507 - 12 5.1831 4.1429 3.0930 0.1317 -0.0132 0.0409 0.0318 -0.0004 0.0000 -0.0188 -0.0218 0.840 - 13 6.0123 3.7903 3.4706 0.0332 -0.0182 0.0106 0.0087 -0.0002 0.0000 -0.0233 -0.0227 - 14 6.9353 3.6075 3.3775 -0.0333 -0.0137 -0.0112 -0.0092 0.0000 0.0000 -0.0244 -0.0196 - 15 7.8737 3.4215 3.2389 -0.0814 -0.0099 -0.0289 -0.0238 0.0002 0.0000 -0.0247 -0.0168 -0.789 - 16 8.8172 3.2345 3.0619 -0.1161 -0.0075 -0.0436 -0.0359 0.0003 0.0000 -0.0249 -0.0142 -0.443 - 17 9.7556 3.0486 2.8543 -0.1406 -0.0064 -0.0560 -0.0461 0.0003 0.0000 -0.0250 -0.0120 -0.291 - 18 10.6786 2.8657 2.6240 -0.1568 -0.0062 -0.0664 -0.0547 0.0003 0.0000 -0.0250 -0.0102 -0.207 - 19 11.5760 2.6879 2.3787 -0.1663 -0.0063 -0.0751 -0.0619 0.0003 0.0000 -0.0251 -0.0087 -0.155 - 20 12.4328 2.5181 2.1010 -0.1702 -0.0065 -0.0821 -0.0676 0.0003 0.0000 -0.0252 -0.0075 -0.123 - 21 13.2400 2.3582 1.8520 -0.1693 -0.0069 -0.0872 -0.0718 0.0003 0.0000 -0.0254 -0.0067 -0.104 - 22 13.9941 2.2087 1.6074 -0.1642 -0.0074 -0.0903 -0.0744 0.0002 0.0000 -0.0257 -0.0064 -0.095 - 23 14.6868 2.0715 1.3716 -0.1548 -0.0079 -0.0908 -0.0748 0.0001 0.0000 -0.0261 -0.0067 -0.099 - 24 15.3105 1.9479 1.1479 -0.1412 -0.0083 -0.0880 -0.0725 0.0001 0.0000 -0.0264 -0.0075 -0.114 - 25 15.8583 1.8393 0.9381 -0.1232 -0.0084 -0.0814 -0.0670 -0.0000 0.0000 -0.0261 -0.0084 -0.139 - 26 16.3244 1.7470 0.7427 -0.1016 -0.0083 -0.0707 -0.0582 -0.0000 0.0000 -0.0235 -0.0080 -0.153 - 27 16.6722 1.4928 0.4131 -0.0785 -0.0079 -0.1735 -0.0527 -0.0009 0.0000 -0.0177 -0.0023 -0.086 - 28 16.9098 1.1466 0.2292 -0.0553 -0.0063 -0.1591 -0.0483 -0.0012 0.0000 -0.0185 -0.0032 -0.133 - 29 17.0696 0.9138 0.1104 -0.0324 -0.0044 -0.1172 -0.0356 -0.0017 0.0000 -0.0168 -0.0038 -0.222 - 30 17.1499 0.7967 0.0322 -0.0107 -0.0034 -0.0445 -0.0135 -0.0028 0.0000 -0.0078 -0.0022 -0.332 + 1 0.0114 7.7520 0.3539 0.7898 0.0126 0.1322 0.1027 0.0228 0.0000 -0.0068 -0.0262 0.316 + 2 0.1025 7.6885 1.0491 0.7737 0.0119 0.1298 0.1009 0.0052 0.0000 -0.0067 -0.0259 0.316 + 3 0.2837 7.5620 1.7073 0.7690 0.0105 0.1311 0.1019 0.0040 0.0000 -0.0064 -0.0259 0.313 + 4 0.5530 7.3741 2.3052 0.7585 0.0082 0.1326 0.1030 0.0034 0.0000 -0.0061 -0.0259 0.309 + 5 0.9075 7.1267 2.8223 0.7371 0.0057 0.1333 0.1036 0.0029 0.0000 -0.0058 -0.0258 0.306 + 6 1.3432 6.8226 3.2414 0.7007 0.0062 0.1323 0.1028 0.0023 0.0000 -0.0058 -0.0256 0.306 + 7 1.8554 6.4651 3.5491 0.6456 0.0159 0.1286 0.1000 0.0015 0.0000 -0.0061 -0.0253 0.311 + 8 2.4386 6.0582 3.7368 0.5700 0.0235 0.1212 0.0942 0.0009 0.0000 -0.0069 -0.0247 0.323 + 9 3.0862 5.6062 3.8005 0.4745 0.0165 0.1090 0.0847 0.0002 0.0000 -0.0084 -0.0240 0.349 + 10 3.7613 5.1351 3.4440 0.3668 0.0064 0.0920 0.0715 -0.0001 0.0000 -0.0105 -0.0231 0.397 + 11 4.4532 4.6522 3.3149 0.2538 -0.0030 0.0702 0.0546 -0.0004 0.0000 -0.0134 -0.0220 0.495 + 12 5.1831 4.1429 3.0930 0.1366 -0.0140 0.0424 0.0330 -0.0004 0.0000 -0.0176 -0.0211 0.784 + 13 6.0123 3.7903 3.4706 0.0364 -0.0187 0.0117 0.0096 -0.0002 0.0000 -0.0216 -0.0214 + 14 6.9353 3.6075 3.3775 -0.0307 -0.0140 -0.0103 -0.0085 0.0000 0.0000 -0.0225 -0.0181 + 15 7.8737 3.4215 3.2389 -0.0791 -0.0101 -0.0281 -0.0231 0.0002 0.0000 -0.0228 -0.0152 -0.736 + 16 8.8172 3.2345 3.0619 -0.1142 -0.0076 -0.0429 -0.0353 0.0003 0.0000 -0.0229 -0.0126 -0.399 + 17 9.7556 3.0486 2.8543 -0.1390 -0.0065 -0.0554 -0.0456 0.0003 0.0000 -0.0230 -0.0104 -0.254 + 18 10.6786 2.8657 2.6239 -0.1554 -0.0063 -0.0659 -0.0543 0.0003 0.0000 -0.0230 -0.0085 -0.174 + 19 11.5760 2.6879 2.3787 -0.1651 -0.0063 -0.0746 -0.0615 0.0003 0.0000 -0.0231 -0.0070 -0.126 + 20 12.4328 2.5181 2.1010 -0.1692 -0.0066 -0.0816 -0.0672 0.0003 0.0000 -0.0232 -0.0058 -0.095 + 21 13.2400 2.3582 1.8520 -0.1685 -0.0070 -0.0868 -0.0715 0.0003 0.0000 -0.0234 -0.0050 -0.077 + 22 13.9941 2.2087 1.6074 -0.1636 -0.0074 -0.0899 -0.0741 0.0002 0.0000 -0.0236 -0.0047 -0.069 + 23 14.6868 2.0715 1.3716 -0.1545 -0.0079 -0.0906 -0.0746 0.0002 0.0000 -0.0240 -0.0049 -0.072 + 24 15.3105 1.9479 1.1479 -0.1411 -0.0084 -0.0880 -0.0725 0.0001 0.0000 -0.0244 -0.0057 -0.087 + 25 15.8583 1.8393 0.9381 -0.1235 -0.0085 -0.0815 -0.0672 0.0000 0.0000 -0.0241 -0.0066 -0.108 + 26 16.3244 1.7470 0.7427 -0.1024 -0.0087 -0.0712 -0.0586 0.0000 0.0000 -0.0215 -0.0062 -0.116 + 27 16.6722 1.4928 0.4131 -0.0792 -0.0083 -0.1750 -0.0531 -0.0009 0.0000 -0.0161 -0.0015 -0.053 + 28 16.9098 1.1466 0.2292 -0.0556 -0.0064 -0.1600 -0.0486 -0.0012 0.0000 -0.0172 -0.0025 -0.104 + 29 17.0696 0.9138 0.1104 -0.0325 -0.0043 -0.1176 -0.0357 -0.0017 0.0000 -0.0160 -0.0034 -0.197 + 30 17.1499 0.7967 0.0322 -0.0106 -0.0026 -0.0443 -0.0134 -0.0026 0.0000 -0.0076 -0.0021 -0.316 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.01064 Clsurf = -0.00256 - CYsurf = -0.00003 Cmsurf = 0.00227 - CDsurf = 0.00044 Cnsurf = 0.00019 + CLsurf = 0.01138 Clsurf = -0.00249 + CYsurf = 0.00000 Cmsurf = 0.00187 + CDsurf = 0.00044 Cnsurf = 0.00018 CDisurf = 0.00044 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.02071 CDsurf = 0.00085 + CLsurf = 0.02217 CDsurf = 0.00086 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 0.7719 0.0128 0.1292 0.1004 0.0230 0.0000 -0.0053 0.0245 0.302 - 32 -0.1025 7.6885 1.0492 0.7565 0.0120 0.1269 0.0986 0.0052 0.0000 -0.0053 0.0243 0.304 - 33 -0.2837 7.5620 1.7073 0.7516 0.0103 0.1282 0.0996 0.0040 0.0000 -0.0050 0.0243 0.300 - 34 -0.5530 7.3741 2.3052 0.7408 0.0078 0.1295 0.1006 0.0034 0.0000 -0.0046 0.0242 0.296 - 35 -0.9075 7.1267 2.8223 0.7192 0.0051 0.1301 0.1011 0.0029 0.0000 -0.0043 0.0240 0.293 - 36 -1.3432 6.8226 3.2414 0.6828 0.0055 0.1289 0.1002 0.0022 0.0000 -0.0043 0.0239 0.293 - 37 -1.8554 6.4651 3.5491 0.6282 0.0152 0.1252 0.0973 0.0016 0.0000 -0.0047 0.0236 0.298 - 38 -2.4386 6.0582 3.7368 0.5533 0.0227 0.1176 0.0914 0.0008 0.0000 -0.0056 0.0231 0.311 - 39 -3.0862 5.6062 3.8005 0.4585 0.0153 0.1053 0.0818 0.0002 0.0000 -0.0072 0.0225 0.338 - 40 -3.7613 5.1351 3.4440 0.3532 0.0055 0.0886 0.0688 -0.0002 0.0000 -0.0098 0.0219 0.392 - 41 -4.4532 4.6522 3.3149 0.2443 -0.0029 0.0676 0.0525 -0.0004 0.0000 -0.0135 0.0217 0.507 - 42 -5.1831 4.1429 3.0930 0.1317 -0.0132 0.0409 0.0318 -0.0004 0.0000 -0.0188 0.0218 0.840 - 43 -6.0123 3.7903 3.4706 0.0332 -0.0182 0.0106 0.0087 -0.0002 0.0000 -0.0233 0.0227 - 44 -6.9353 3.6075 3.3775 -0.0333 -0.0137 -0.0112 -0.0092 0.0000 0.0000 -0.0244 0.0196 - 45 -7.8737 3.4215 3.2389 -0.0814 -0.0099 -0.0289 -0.0238 0.0002 0.0000 -0.0247 0.0168 -0.789 - 46 -8.8172 3.2345 3.0619 -0.1161 -0.0075 -0.0436 -0.0359 0.0003 0.0000 -0.0249 0.0142 -0.443 - 47 -9.7556 3.0486 2.8543 -0.1406 -0.0064 -0.0560 -0.0461 0.0003 0.0000 -0.0250 0.0120 -0.291 - 48 -10.6786 2.8657 2.6240 -0.1568 -0.0062 -0.0664 -0.0547 0.0003 0.0000 -0.0250 0.0102 -0.207 - 49 -11.5760 2.6879 2.3787 -0.1663 -0.0063 -0.0751 -0.0619 0.0003 0.0000 -0.0251 0.0087 -0.155 - 50 -12.4328 2.5181 2.1010 -0.1702 -0.0065 -0.0821 -0.0676 0.0003 0.0000 -0.0252 0.0075 -0.123 - 51 -13.2400 2.3582 1.8520 -0.1693 -0.0069 -0.0872 -0.0718 0.0003 0.0000 -0.0254 0.0067 -0.104 - 52 -13.9941 2.2087 1.6074 -0.1642 -0.0074 -0.0903 -0.0744 0.0002 0.0000 -0.0257 0.0064 -0.095 - 53 -14.6868 2.0715 1.3716 -0.1548 -0.0079 -0.0908 -0.0748 0.0001 0.0000 -0.0261 0.0067 -0.099 - 54 -15.3105 1.9479 1.1479 -0.1412 -0.0083 -0.0880 -0.0725 0.0001 0.0000 -0.0264 0.0075 -0.114 - 55 -15.8583 1.8393 0.9381 -0.1232 -0.0084 -0.0814 -0.0670 -0.0000 0.0000 -0.0261 0.0084 -0.139 - 56 -16.3244 1.7470 0.7427 -0.1016 -0.0083 -0.0707 -0.0582 -0.0000 0.0000 -0.0235 0.0080 -0.153 - 57 -16.6722 1.4928 0.4131 -0.0785 -0.0079 -0.1735 -0.0527 -0.0009 0.0000 -0.0177 0.0023 -0.086 - 58 -16.9098 1.1466 0.2292 -0.0553 -0.0063 -0.1591 -0.0483 -0.0012 0.0000 -0.0185 0.0032 -0.133 - 59 -17.0696 0.9138 0.1104 -0.0324 -0.0044 -0.1172 -0.0356 -0.0017 0.0000 -0.0168 0.0038 -0.222 - 60 -17.1499 0.7967 0.0322 -0.0107 -0.0034 -0.0445 -0.0135 -0.0028 0.0000 -0.0078 0.0022 -0.332 + 31 -0.0114 7.7520 0.3539 0.7898 0.0126 0.1322 0.1027 0.0228 0.0000 -0.0068 0.0262 0.316 + 32 -0.1025 7.6885 1.0491 0.7737 0.0119 0.1298 0.1009 0.0052 0.0000 -0.0067 0.0259 0.316 + 33 -0.2837 7.5620 1.7073 0.7690 0.0105 0.1311 0.1019 0.0040 0.0000 -0.0064 0.0259 0.313 + 34 -0.5530 7.3741 2.3052 0.7585 0.0082 0.1326 0.1030 0.0034 0.0000 -0.0061 0.0259 0.309 + 35 -0.9075 7.1267 2.8223 0.7371 0.0057 0.1333 0.1036 0.0029 0.0000 -0.0058 0.0258 0.306 + 36 -1.3432 6.8226 3.2414 0.7007 0.0062 0.1323 0.1028 0.0023 0.0000 -0.0058 0.0256 0.306 + 37 -1.8554 6.4651 3.5491 0.6456 0.0159 0.1286 0.1000 0.0015 0.0000 -0.0061 0.0253 0.311 + 38 -2.4386 6.0582 3.7368 0.5700 0.0235 0.1212 0.0942 0.0009 0.0000 -0.0069 0.0247 0.323 + 39 -3.0862 5.6062 3.8005 0.4745 0.0165 0.1090 0.0847 0.0002 0.0000 -0.0084 0.0240 0.349 + 40 -3.7613 5.1351 3.4440 0.3668 0.0064 0.0920 0.0715 -0.0001 0.0000 -0.0105 0.0231 0.397 + 41 -4.4532 4.6522 3.3149 0.2538 -0.0030 0.0702 0.0546 -0.0004 0.0000 -0.0134 0.0220 0.495 + 42 -5.1831 4.1429 3.0930 0.1366 -0.0140 0.0424 0.0330 -0.0004 0.0000 -0.0176 0.0211 0.784 + 43 -6.0123 3.7903 3.4706 0.0364 -0.0187 0.0117 0.0096 -0.0002 0.0000 -0.0216 0.0214 + 44 -6.9353 3.6075 3.3775 -0.0307 -0.0140 -0.0103 -0.0085 0.0000 0.0000 -0.0225 0.0181 + 45 -7.8737 3.4215 3.2389 -0.0791 -0.0101 -0.0281 -0.0231 0.0002 0.0000 -0.0228 0.0152 -0.736 + 46 -8.8172 3.2345 3.0619 -0.1142 -0.0076 -0.0429 -0.0353 0.0003 0.0000 -0.0229 0.0126 -0.399 + 47 -9.7556 3.0486 2.8543 -0.1390 -0.0065 -0.0554 -0.0456 0.0003 0.0000 -0.0230 0.0104 -0.254 + 48 -10.6786 2.8657 2.6239 -0.1554 -0.0063 -0.0659 -0.0543 0.0003 0.0000 -0.0230 0.0085 -0.174 + 49 -11.5760 2.6879 2.3787 -0.1651 -0.0063 -0.0746 -0.0615 0.0003 0.0000 -0.0231 0.0070 -0.126 + 50 -12.4328 2.5181 2.1010 -0.1692 -0.0066 -0.0816 -0.0672 0.0003 0.0000 -0.0232 0.0058 -0.095 + 51 -13.2400 2.3582 1.8520 -0.1685 -0.0070 -0.0868 -0.0715 0.0003 0.0000 -0.0234 0.0050 -0.077 + 52 -13.9941 2.2087 1.6074 -0.1636 -0.0074 -0.0899 -0.0741 0.0002 0.0000 -0.0236 0.0047 -0.069 + 53 -14.6868 2.0715 1.3716 -0.1545 -0.0079 -0.0906 -0.0746 0.0002 0.0000 -0.0240 0.0049 -0.072 + 54 -15.3105 1.9479 1.1479 -0.1411 -0.0084 -0.0880 -0.0725 0.0001 0.0000 -0.0244 0.0057 -0.087 + 55 -15.8583 1.8393 0.9381 -0.1235 -0.0085 -0.0815 -0.0672 0.0000 0.0000 -0.0241 0.0066 -0.108 + 56 -16.3244 1.7470 0.7427 -0.1024 -0.0087 -0.0712 -0.0586 0.0000 0.0000 -0.0215 0.0062 -0.116 + 57 -16.6722 1.4928 0.4131 -0.0792 -0.0083 -0.1750 -0.0531 -0.0009 0.0000 -0.0161 0.0015 -0.053 + 58 -16.9098 1.1466 0.2292 -0.0556 -0.0064 -0.1600 -0.0486 -0.0012 0.0000 -0.0172 0.0025 -0.104 + 59 -17.0696 0.9138 0.1104 -0.0325 -0.0043 -0.1176 -0.0357 -0.0017 0.0000 -0.0160 0.0034 -0.197 + 60 -17.1499 0.7967 0.0322 -0.0106 -0.0026 -0.0443 -0.0134 -0.0026 0.0000 -0.0076 0.0021 -0.316 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.03263 Clsurf = 0.00320 - CYsurf = 0.00522 Cmsurf = 0.15666 - CDsurf = 0.00018 Cnsurf = -0.00322 - CDisurf = 0.00018 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.03282 Clsurf = 0.00322 + CYsurf = 0.00526 Cmsurf = 0.15754 + CDsurf = 0.00017 Cnsurf = -0.00324 + CDisurf = 0.00017 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.19889 CDsurf = 0.00106 + CLsurf = -0.20003 CDsurf = 0.00102 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.6261 -0.0217 -0.1843 -0.1438 0.0844 0.0000 0.0109 0.0398 0.326 - 62 0.0418 4.2566 0.2392 -0.7456 -0.0223 -0.2243 -0.1749 0.0099 0.0000 0.0108 0.0457 0.312 - 63 0.1156 4.2274 0.3930 -0.7547 -0.0228 -0.2288 -0.1785 0.0048 0.0000 0.0103 0.0460 0.308 - 64 0.2254 4.1839 0.5386 -0.7573 -0.0232 -0.2321 -0.1810 0.0037 0.0000 0.0094 0.0458 0.302 - 65 0.3698 4.1268 0.6730 -0.7579 -0.0233 -0.2355 -0.1837 0.0031 0.0000 0.0082 0.0453 0.295 - 66 0.5474 4.0565 0.7936 -0.7576 -0.0231 -0.2395 -0.1868 0.0028 0.0000 0.0069 0.0448 0.287 - 67 0.7617 3.9717 0.9441 -0.7556 -0.0226 -0.2440 -0.1903 0.0023 0.0000 0.0056 0.0444 0.279 - 68 1.0116 3.8728 1.0344 -0.7512 -0.0214 -0.2488 -0.1940 0.0018 0.0000 0.0043 0.0441 0.272 - 69 1.2891 3.7630 1.1046 -0.7450 -0.0196 -0.2540 -0.1981 0.0015 0.0000 0.0031 0.0440 0.266 - 70 1.5912 3.6435 1.1542 -0.7355 -0.0173 -0.2589 -0.2019 0.0010 0.0000 0.0021 0.0440 0.261 - 71 1.9146 3.5155 1.1831 -0.7224 -0.0150 -0.2636 -0.2056 0.0008 0.0000 0.0013 0.0440 0.256 - 72 2.2558 3.3805 1.1921 -0.7064 -0.0132 -0.2681 -0.2091 0.0004 0.0000 0.0006 0.0442 0.253 - 73 2.6109 3.2400 1.1821 -0.6861 -0.0122 -0.2717 -0.2119 0.0002 0.0000 0.0001 0.0443 0.250 - 74 2.9762 3.0955 1.1548 -0.6628 -0.0120 -0.2747 -0.2142 0.0001 0.0000 -0.0004 0.0444 0.248 - 75 3.3476 2.9485 1.1122 -0.6363 -0.0123 -0.2769 -0.2159 -0.0001 0.0000 -0.0008 0.0444 0.246 - 76 3.7210 2.8008 1.0564 -0.6070 -0.0129 -0.2781 -0.2169 -0.0002 0.0000 -0.0011 0.0443 0.245 - 77 4.0924 2.6538 0.9900 -0.5756 -0.0137 -0.2783 -0.2170 -0.0003 0.0000 -0.0015 0.0441 0.243 - 78 4.4577 2.5093 0.9155 -0.5423 -0.0146 -0.2773 -0.2163 -0.0003 0.0000 -0.0019 0.0436 0.241 - 79 4.8128 2.3687 0.8353 -0.5081 -0.0156 -0.2752 -0.2146 -0.0004 0.0000 -0.0024 0.0428 0.239 - 80 5.1540 2.2338 0.7518 -0.4730 -0.0167 -0.2717 -0.2119 -0.0004 0.0000 -0.0030 0.0417 0.236 - 81 5.4774 2.1058 0.6671 -0.4366 -0.0180 -0.2661 -0.2075 -0.0004 0.0000 -0.0039 0.0400 0.231 - 82 5.7795 1.9862 0.5830 -0.3998 -0.0193 -0.2583 -0.2014 -0.0006 0.0000 -0.0050 0.0378 0.225 - 83 6.0570 1.8764 0.5012 -0.3617 -0.0207 -0.2474 -0.1929 -0.0007 0.0000 -0.0064 0.0349 0.217 - 84 6.3069 1.7776 0.4225 -0.3226 -0.0221 -0.2329 -0.1816 -0.0008 0.0000 -0.0079 0.0312 0.207 - 85 6.5264 1.6907 0.3478 -0.2820 -0.0234 -0.2141 -0.1669 -0.0009 0.0000 -0.0094 0.0269 0.194 - 86 6.7314 1.6096 0.3326 -0.2377 -0.0247 -0.1895 -0.1478 -0.0010 0.0000 -0.0107 0.0218 0.178 - 87 6.9144 1.5372 0.2507 -0.1880 -0.0259 -0.1569 -0.1224 -0.0012 0.0000 -0.0112 0.0161 0.159 - 88 7.0535 1.4822 0.1746 -0.1360 -0.0267 -0.1178 -0.0919 -0.0013 0.0000 -0.0102 0.0106 0.139 - 89 7.1471 1.4451 0.1029 -0.0823 -0.0273 -0.0731 -0.0570 -0.0012 0.0000 -0.0073 0.0057 0.123 - 90 7.1941 1.4265 0.0340 -0.0275 -0.0277 -0.0248 -0.0193 -0.0010 0.0000 -0.0026 0.0018 0.114 + 61 0.0047 4.2713 0.0803 -0.6294 -0.0216 -0.1853 -0.1445 0.0855 0.0000 0.0109 0.0400 0.326 + 62 0.0418 4.2566 0.2392 -0.7504 -0.0222 -0.2257 -0.1761 0.0100 0.0000 0.0109 0.0460 0.312 + 63 0.1156 4.2274 0.3930 -0.7599 -0.0227 -0.2304 -0.1797 0.0048 0.0000 0.0104 0.0463 0.308 + 64 0.2254 4.1839 0.5386 -0.7626 -0.0230 -0.2337 -0.1822 0.0036 0.0000 0.0095 0.0461 0.302 + 65 0.3698 4.1268 0.6730 -0.7630 -0.0232 -0.2371 -0.1849 0.0031 0.0000 0.0083 0.0456 0.295 + 66 0.5474 4.0565 0.7936 -0.7626 -0.0230 -0.2411 -0.1880 0.0027 0.0000 0.0069 0.0451 0.287 + 67 0.7617 3.9717 0.9441 -0.7604 -0.0225 -0.2455 -0.1915 0.0022 0.0000 0.0056 0.0447 0.279 + 68 1.0116 3.8728 1.0344 -0.7568 -0.0213 -0.2506 -0.1955 0.0018 0.0000 0.0043 0.0444 0.272 + 69 1.2891 3.7630 1.1046 -0.7502 -0.0195 -0.2557 -0.1994 0.0014 0.0000 0.0031 0.0443 0.266 + 70 1.5912 3.6435 1.1542 -0.7404 -0.0172 -0.2607 -0.2033 0.0010 0.0000 0.0021 0.0442 0.260 + 71 1.9146 3.5155 1.1831 -0.7274 -0.0149 -0.2654 -0.2070 0.0007 0.0000 0.0013 0.0443 0.256 + 72 2.2558 3.3805 1.1921 -0.7111 -0.0131 -0.2699 -0.2105 0.0004 0.0000 0.0006 0.0444 0.253 + 73 2.6109 3.2400 1.1821 -0.6906 -0.0121 -0.2735 -0.2133 0.0002 0.0000 0.0000 0.0446 0.250 + 74 2.9762 3.0955 1.1548 -0.6668 -0.0119 -0.2764 -0.2155 0.0000 0.0000 -0.0004 0.0446 0.248 + 75 3.3476 2.9485 1.1122 -0.6400 -0.0122 -0.2785 -0.2172 -0.0001 0.0000 -0.0008 0.0447 0.246 + 76 3.7210 2.8008 1.0564 -0.6104 -0.0128 -0.2796 -0.2181 -0.0002 0.0000 -0.0012 0.0446 0.245 + 77 4.0924 2.6538 0.9900 -0.5786 -0.0136 -0.2797 -0.2182 -0.0003 0.0000 -0.0015 0.0443 0.243 + 78 4.4577 2.5093 0.9155 -0.5451 -0.0145 -0.2787 -0.2174 -0.0004 0.0000 -0.0019 0.0438 0.241 + 79 4.8128 2.3687 0.8353 -0.5104 -0.0155 -0.2765 -0.2156 -0.0004 0.0000 -0.0024 0.0430 0.239 + 80 5.1540 2.2338 0.7518 -0.4748 -0.0167 -0.2727 -0.2127 -0.0004 0.0000 -0.0031 0.0418 0.236 + 81 5.4774 2.1058 0.6671 -0.4384 -0.0179 -0.2671 -0.2083 -0.0005 0.0000 -0.0039 0.0402 0.231 + 82 5.7795 1.9862 0.5830 -0.4012 -0.0193 -0.2592 -0.2021 -0.0007 0.0000 -0.0050 0.0379 0.225 + 83 6.0570 1.8764 0.5012 -0.3629 -0.0207 -0.2482 -0.1936 -0.0007 0.0000 -0.0064 0.0350 0.217 + 84 6.3069 1.7776 0.4225 -0.3236 -0.0221 -0.2336 -0.1822 -0.0008 0.0000 -0.0079 0.0313 0.207 + 85 6.5264 1.6907 0.3478 -0.2828 -0.0234 -0.2147 -0.1674 -0.0010 0.0000 -0.0094 0.0270 0.194 + 86 6.7314 1.6096 0.3326 -0.2383 -0.0247 -0.1900 -0.1482 -0.0011 0.0000 -0.0107 0.0219 0.178 + 87 6.9144 1.5372 0.2507 -0.1885 -0.0258 -0.1574 -0.1227 -0.0012 0.0000 -0.0112 0.0161 0.159 + 88 7.0535 1.4822 0.1746 -0.1363 -0.0267 -0.1181 -0.0921 -0.0013 0.0000 -0.0102 0.0106 0.139 + 89 7.1471 1.4451 0.1029 -0.0825 -0.0273 -0.0733 -0.0572 -0.0012 0.0000 -0.0073 0.0058 0.123 + 90 7.1941 1.4265 0.0340 -0.0276 -0.0277 -0.0249 -0.0194 -0.0010 0.0000 -0.0026 0.0018 0.114 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.03263 Clsurf = -0.00320 - CYsurf = -0.00522 Cmsurf = 0.15666 - CDsurf = 0.00018 Cnsurf = 0.00322 - CDisurf = 0.00018 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.03282 Clsurf = -0.00322 + CYsurf = -0.00526 Cmsurf = 0.15754 + CDsurf = 0.00017 Cnsurf = 0.00324 + CDisurf = 0.00017 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.19888 CDsurf = 0.00106 + CLsurf = -0.20003 CDsurf = 0.00102 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.6261 -0.0218 -0.1843 -0.1438 0.0844 0.0000 0.0109 -0.0398 0.326 - 92 -0.0418 4.2566 0.2392 -0.7456 -0.0223 -0.2243 -0.1749 0.0099 0.0000 0.0108 -0.0457 0.312 - 93 -0.1156 4.2274 0.3930 -0.7547 -0.0228 -0.2288 -0.1785 0.0048 0.0000 0.0103 -0.0460 0.308 - 94 -0.2254 4.1839 0.5386 -0.7573 -0.0232 -0.2321 -0.1810 0.0037 0.0000 0.0094 -0.0458 0.302 - 95 -0.3698 4.1268 0.6730 -0.7579 -0.0233 -0.2355 -0.1837 0.0031 0.0000 0.0082 -0.0453 0.295 - 96 -0.5474 4.0565 0.7936 -0.7576 -0.0231 -0.2395 -0.1868 0.0028 0.0000 0.0069 -0.0448 0.287 - 97 -0.7617 3.9717 0.9441 -0.7556 -0.0226 -0.2440 -0.1903 0.0023 0.0000 0.0056 -0.0444 0.279 - 98 -1.0116 3.8728 1.0344 -0.7512 -0.0214 -0.2488 -0.1940 0.0018 0.0000 0.0043 -0.0441 0.272 - 99 -1.2891 3.7630 1.1046 -0.7450 -0.0196 -0.2539 -0.1980 0.0015 0.0000 0.0031 -0.0440 0.266 - 100 -1.5912 3.6435 1.1542 -0.7355 -0.0173 -0.2589 -0.2019 0.0010 0.0000 0.0021 -0.0440 0.261 - 101 -1.9146 3.5155 1.1831 -0.7224 -0.0150 -0.2636 -0.2056 0.0008 0.0000 0.0013 -0.0440 0.256 - 102 -2.2558 3.3805 1.1921 -0.7064 -0.0132 -0.2681 -0.2091 0.0004 0.0000 0.0006 -0.0442 0.253 - 103 -2.6109 3.2400 1.1821 -0.6861 -0.0122 -0.2717 -0.2119 0.0002 0.0000 0.0001 -0.0443 0.250 - 104 -2.9762 3.0955 1.1548 -0.6628 -0.0120 -0.2747 -0.2142 0.0001 0.0000 -0.0004 -0.0444 0.248 - 105 -3.3476 2.9485 1.1122 -0.6363 -0.0123 -0.2769 -0.2159 -0.0001 0.0000 -0.0008 -0.0444 0.246 - 106 -3.7210 2.8008 1.0564 -0.6070 -0.0129 -0.2781 -0.2169 -0.0002 0.0000 -0.0011 -0.0443 0.245 - 107 -4.0924 2.6538 0.9900 -0.5756 -0.0137 -0.2783 -0.2170 -0.0003 0.0000 -0.0015 -0.0440 0.243 - 108 -4.4577 2.5093 0.9155 -0.5423 -0.0146 -0.2773 -0.2163 -0.0003 0.0000 -0.0019 -0.0436 0.241 - 109 -4.8128 2.3687 0.8353 -0.5081 -0.0156 -0.2752 -0.2146 -0.0004 0.0000 -0.0024 -0.0428 0.239 - 110 -5.1540 2.2338 0.7518 -0.4730 -0.0167 -0.2717 -0.2119 -0.0004 0.0000 -0.0030 -0.0417 0.236 - 111 -5.4774 2.1058 0.6671 -0.4366 -0.0179 -0.2660 -0.2075 -0.0004 0.0000 -0.0039 -0.0400 0.231 - 112 -5.7795 1.9862 0.5830 -0.3998 -0.0193 -0.2583 -0.2014 -0.0006 0.0000 -0.0050 -0.0378 0.225 - 113 -6.0570 1.8764 0.5012 -0.3617 -0.0207 -0.2474 -0.1929 -0.0007 0.0000 -0.0064 -0.0349 0.217 - 114 -6.3069 1.7776 0.4225 -0.3226 -0.0221 -0.2329 -0.1816 -0.0008 0.0000 -0.0079 -0.0312 0.207 - 115 -6.5264 1.6907 0.3478 -0.2820 -0.0234 -0.2140 -0.1669 -0.0009 0.0000 -0.0094 -0.0269 0.194 - 116 -6.7314 1.6096 0.3326 -0.2377 -0.0247 -0.1895 -0.1478 -0.0010 0.0000 -0.0107 -0.0218 0.178 - 117 -6.9144 1.5372 0.2507 -0.1879 -0.0259 -0.1569 -0.1224 -0.0012 0.0000 -0.0112 -0.0161 0.159 - 118 -7.0535 1.4822 0.1746 -0.1360 -0.0267 -0.1178 -0.0919 -0.0013 0.0000 -0.0102 -0.0106 0.139 - 119 -7.1471 1.4451 0.1029 -0.0823 -0.0273 -0.0731 -0.0570 -0.0012 0.0000 -0.0073 -0.0057 0.123 - 120 -7.1941 1.4265 0.0340 -0.0275 -0.0277 -0.0248 -0.0193 -0.0010 0.0000 -0.0026 -0.0018 0.114 + 91 -0.0047 4.2713 0.0803 -0.6294 -0.0216 -0.1853 -0.1445 0.0855 0.0000 0.0109 -0.0400 0.326 + 92 -0.0418 4.2566 0.2392 -0.7504 -0.0222 -0.2257 -0.1761 0.0100 0.0000 0.0109 -0.0460 0.312 + 93 -0.1156 4.2274 0.3930 -0.7599 -0.0227 -0.2304 -0.1797 0.0048 0.0000 0.0104 -0.0463 0.308 + 94 -0.2254 4.1839 0.5386 -0.7626 -0.0230 -0.2337 -0.1822 0.0036 0.0000 0.0095 -0.0461 0.302 + 95 -0.3698 4.1268 0.6730 -0.7630 -0.0232 -0.2371 -0.1849 0.0031 0.0000 0.0083 -0.0456 0.295 + 96 -0.5474 4.0565 0.7936 -0.7626 -0.0230 -0.2411 -0.1880 0.0027 0.0000 0.0069 -0.0451 0.287 + 97 -0.7617 3.9717 0.9441 -0.7604 -0.0225 -0.2455 -0.1915 0.0022 0.0000 0.0056 -0.0447 0.279 + 98 -1.0116 3.8728 1.0344 -0.7568 -0.0213 -0.2506 -0.1955 0.0018 0.0000 0.0043 -0.0444 0.272 + 99 -1.2891 3.7630 1.1046 -0.7502 -0.0195 -0.2557 -0.1994 0.0014 0.0000 0.0031 -0.0443 0.266 + 100 -1.5912 3.6435 1.1542 -0.7404 -0.0172 -0.2607 -0.2033 0.0010 0.0000 0.0021 -0.0442 0.260 + 101 -1.9146 3.5155 1.1831 -0.7274 -0.0149 -0.2654 -0.2070 0.0007 0.0000 0.0013 -0.0443 0.256 + 102 -2.2558 3.3805 1.1921 -0.7111 -0.0131 -0.2699 -0.2105 0.0004 0.0000 0.0006 -0.0444 0.253 + 103 -2.6109 3.2400 1.1821 -0.6906 -0.0121 -0.2735 -0.2133 0.0002 0.0000 0.0000 -0.0446 0.250 + 104 -2.9762 3.0955 1.1548 -0.6668 -0.0119 -0.2764 -0.2155 0.0000 0.0000 -0.0004 -0.0446 0.248 + 105 -3.3476 2.9485 1.1122 -0.6400 -0.0122 -0.2785 -0.2172 -0.0001 0.0000 -0.0008 -0.0446 0.246 + 106 -3.7210 2.8008 1.0564 -0.6104 -0.0128 -0.2796 -0.2181 -0.0002 0.0000 -0.0012 -0.0446 0.245 + 107 -4.0924 2.6538 0.9900 -0.5786 -0.0136 -0.2797 -0.2182 -0.0003 0.0000 -0.0015 -0.0443 0.243 + 108 -4.4577 2.5093 0.9155 -0.5451 -0.0145 -0.2787 -0.2174 -0.0004 0.0000 -0.0019 -0.0438 0.241 + 109 -4.8128 2.3687 0.8353 -0.5104 -0.0155 -0.2765 -0.2156 -0.0004 0.0000 -0.0024 -0.0430 0.239 + 110 -5.1540 2.2338 0.7518 -0.4748 -0.0167 -0.2727 -0.2127 -0.0004 0.0000 -0.0031 -0.0418 0.236 + 111 -5.4774 2.1058 0.6671 -0.4384 -0.0179 -0.2671 -0.2083 -0.0005 0.0000 -0.0039 -0.0402 0.231 + 112 -5.7795 1.9862 0.5830 -0.4012 -0.0193 -0.2592 -0.2021 -0.0007 0.0000 -0.0050 -0.0379 0.225 + 113 -6.0570 1.8764 0.5012 -0.3629 -0.0207 -0.2482 -0.1936 -0.0007 0.0000 -0.0064 -0.0350 0.217 + 114 -6.3069 1.7776 0.4225 -0.3236 -0.0221 -0.2336 -0.1822 -0.0008 0.0000 -0.0079 -0.0313 0.207 + 115 -6.5264 1.6907 0.3478 -0.2828 -0.0234 -0.2147 -0.1674 -0.0010 0.0000 -0.0094 -0.0270 0.194 + 116 -6.7314 1.6096 0.3326 -0.2383 -0.0247 -0.1900 -0.1482 -0.0011 0.0000 -0.0107 -0.0219 0.178 + 117 -6.9144 1.5372 0.2507 -0.1885 -0.0258 -0.1574 -0.1227 -0.0012 0.0000 -0.0112 -0.0161 0.159 + 118 -7.0535 1.4822 0.1746 -0.1363 -0.0267 -0.1180 -0.0921 -0.0013 0.0000 -0.0102 -0.0106 0.139 + 119 -7.1471 1.4451 0.1029 -0.0825 -0.0273 -0.0733 -0.0572 -0.0012 0.0000 -0.0073 -0.0058 0.123 + 120 -7.1941 1.4265 0.0340 -0.0276 -0.0277 -0.0249 -0.0194 -0.0010 0.0000 -0.0026 -0.0018 0.114 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = -0.00000 Cmsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00000 CDsurf = 0.00000 Cnsurf = 0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.771 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.766 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.756 - 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.742 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.724 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.701 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.671 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.628 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.575 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.507 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.451 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.422 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.399 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.377 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.354 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.336 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.322 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.304 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.296 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.285 - 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.273 - 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.261 - 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.249 - 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.237 - 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.224 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.205 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.183 - 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.162 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.145 - 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.135 + 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.792 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.785 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.773 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.756 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.734 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.716 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.685 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.642 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.591 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.524 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.469 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.440 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.410 + 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.385 + 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.365 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.342 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.325 + 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.313 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.302 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.286 + 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.277 + 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.268 + 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.253 + 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.239 + 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.225 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.206 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.186 + 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.164 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.147 + 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.138 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00968 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.02521 + CLsurf = -0.00975 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.02514 CDsurf = 0.00022 Cnsurf = 0.00000 CDisurf = 0.00022 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00976 CDsurf = 0.00022 + CLsurf = -0.00983 CDsurf = 0.00022 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.2462 -0.0623 -0.1151 -0.0093 0.0000 0.0000 -0.0004 0.0003 0.210 - 152 -1.3090 31.2096 11.6724 -0.3309 -0.0594 -0.0412 -0.0106 0.0002 0.0000 -0.0008 0.0005 0.171 - 153 -0.9350 34.0626 12.7394 -0.3452 -0.0329 -0.0247 -0.0101 0.0002 0.0000 -0.0018 0.0003 0.075 - 154 -0.5610 36.1619 13.5246 -0.3468 -0.0205 -0.0161 -0.0096 0.0003 0.0000 -0.0023 0.0000 0.009 - 155 -0.1870 37.5332 14.0374 -0.3467 -0.0161 -0.0107 -0.0092 0.0003 0.0000 -0.0025 -0.0002 -0.024 - 156 0.1870 37.5332 14.0374 -0.3467 -0.0161 -0.0107 -0.0092 0.0003 0.0000 -0.0025 -0.0002 -0.024 - 157 0.5610 36.1619 13.5246 -0.3468 -0.0205 -0.0161 -0.0096 0.0003 0.0000 -0.0023 0.0000 0.009 - 158 0.9350 34.0626 12.7394 -0.3452 -0.0329 -0.0247 -0.0101 0.0002 0.0000 -0.0018 0.0003 0.075 - 159 1.3090 31.2096 11.6724 -0.3309 -0.0595 -0.0412 -0.0106 0.0002 0.0000 -0.0008 0.0005 0.171 - 160 1.6830 26.5957 9.9468 -0.2462 -0.0623 -0.1151 -0.0093 0.0000 0.0000 -0.0004 0.0003 0.210 + 151 -1.6830 26.5957 9.9468 -0.2480 -0.0624 -0.1160 -0.0093 0.0001 0.0000 -0.0004 0.0003 0.212 + 152 -1.3090 31.2096 11.6724 -0.3333 -0.0595 -0.0415 -0.0107 0.0002 0.0000 -0.0008 0.0005 0.174 + 153 -0.9350 34.0626 12.7394 -0.3477 -0.0328 -0.0249 -0.0102 0.0002 0.0000 -0.0017 0.0003 0.079 + 154 -0.5610 36.1619 13.5246 -0.3492 -0.0202 -0.0162 -0.0097 0.0003 0.0000 -0.0023 0.0001 0.012 + 155 -0.1870 37.5332 14.0374 -0.3492 -0.0158 -0.0108 -0.0093 0.0003 0.0000 -0.0025 -0.0001 -0.021 + 156 0.1870 37.5332 14.0374 -0.3492 -0.0158 -0.0108 -0.0093 0.0003 0.0000 -0.0025 -0.0001 -0.021 + 157 0.5610 36.1619 13.5246 -0.3492 -0.0202 -0.0162 -0.0097 0.0003 0.0000 -0.0023 0.0001 0.012 + 158 0.9350 34.0626 12.7394 -0.3477 -0.0328 -0.0249 -0.0102 0.0002 0.0000 -0.0017 0.0003 0.079 + 159 1.3090 31.2096 11.6724 -0.3333 -0.0595 -0.0415 -0.0107 0.0002 0.0000 -0.0008 0.0005 0.174 + 160 1.6830 26.5957 9.9468 -0.2480 -0.0624 -0.1160 -0.0093 0.0001 0.0000 -0.0004 0.0003 0.212 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.932 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.892 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0002 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.885 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.879 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.874 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.856 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.837 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.803 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.684 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.386 + 161 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.904 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.874 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.877 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.872 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.872 + 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.855 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.837 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.784 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.654 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.364 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_05_02.txt b/regression/scripts/AVL/avl_files/strip_forces_case_05_02.txt index d273f83d82..f430e2a2f8 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_05_02.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_05_02.txt @@ -7,252 +7,252 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.10754 Clsurf = -0.01779 - CYsurf = -0.00750 Cmsurf = -0.08937 - CDsurf = 0.00154 Cnsurf = 0.00082 - CDisurf = 0.00154 CDvsurf = 0.00000 + CLsurf = 0.10830 Clsurf = -0.01787 + CYsurf = -0.00751 Cmsurf = -0.08978 + CDsurf = 0.00153 Cnsurf = 0.00082 + CDisurf = 0.00153 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.21041 CDsurf = 0.00300 + CLsurf = 0.21190 CDsurf = 0.00298 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 1.7916 0.0505 0.2980 0.2311 0.1041 0.0000 -0.0144 -0.0588 0.312 - 2 0.1025 7.6885 1.0492 1.7205 0.0498 0.2885 0.2238 0.0209 0.0000 -0.0144 -0.0573 0.314 - 3 0.2837 7.5620 1.7073 1.7111 0.0481 0.2917 0.2263 0.0155 0.0000 -0.0137 -0.0572 0.310 - 4 0.5530 7.3741 2.3052 1.6983 0.0455 0.2969 0.2303 0.0135 0.0000 -0.0125 -0.0571 0.304 - 5 0.9075 7.1267 2.8223 1.6739 0.0421 0.3028 0.2349 0.0120 0.0000 -0.0113 -0.0570 0.298 - 6 1.3432 6.8226 3.2414 1.6333 0.0397 0.3086 0.2394 0.0102 0.0000 -0.0103 -0.0572 0.293 - 7 1.8554 6.4651 3.5491 1.5715 0.0416 0.3134 0.2431 0.0085 0.0000 -0.0098 -0.0575 0.290 - 8 2.4386 6.0582 3.7368 1.4858 0.0419 0.3162 0.2453 0.0059 0.0000 -0.0099 -0.0581 0.291 - 9 3.0862 5.6062 3.8005 1.3754 0.0332 0.3163 0.2453 0.0033 0.0000 -0.0110 -0.0589 0.295 - 10 3.7613 5.1351 3.4440 1.2501 0.0229 0.3139 0.2434 0.0016 0.0000 -0.0131 -0.0603 0.304 - 11 4.4532 4.6522 3.3149 1.1186 0.0132 0.3100 0.2404 -0.0005 0.0000 -0.0164 -0.0624 0.318 - 12 5.1831 4.1429 3.0930 0.9787 0.0003 0.3046 0.2362 -0.0027 0.0000 -0.0210 -0.0652 0.339 - 13 6.0123 3.7903 3.4706 0.8497 -0.0069 0.2730 0.2242 -0.0034 0.0000 -0.0242 -0.0713 0.358 - 14 6.9353 3.6075 3.3775 0.7562 -0.0038 0.2553 0.2096 -0.0025 0.0000 -0.0249 -0.0687 0.369 - 15 7.8737 3.4215 3.2389 0.6798 -0.0016 0.2420 0.1987 -0.0020 0.0000 -0.0251 -0.0665 0.376 - 16 8.8172 3.2345 3.0619 0.6151 -0.0003 0.2316 0.1902 -0.0017 0.0000 -0.0251 -0.0646 0.382 - 17 9.7556 3.0486 2.8543 0.5589 0.0005 0.2233 0.1833 -0.0015 0.0000 -0.0251 -0.0630 0.387 - 18 10.6786 2.8657 2.6240 0.5093 0.0009 0.2165 0.1777 -0.0013 0.0000 -0.0250 -0.0617 0.391 - 19 11.5760 2.6879 2.3787 0.4650 0.0013 0.2107 0.1730 -0.0012 0.0000 -0.0249 -0.0606 0.394 - 20 12.4328 2.5181 2.1010 0.4250 0.0018 0.2055 0.1688 -0.0011 0.0000 -0.0247 -0.0595 0.397 - 21 13.2400 2.3582 1.8520 0.3883 0.0025 0.2005 0.1647 -0.0010 0.0000 -0.0245 -0.0584 0.399 - 22 13.9941 2.2087 1.6074 0.3538 0.0034 0.1951 0.1602 -0.0009 0.0000 -0.0241 -0.0570 0.401 - 23 14.6868 2.0715 1.3716 0.3203 0.0048 0.1883 0.1546 -0.0008 0.0000 -0.0235 -0.0553 0.402 - 24 15.3105 1.9479 1.1479 0.2865 0.0065 0.1792 0.1471 -0.0007 0.0000 -0.0226 -0.0527 0.403 - 25 15.8583 1.8393 0.9381 0.2507 0.0086 0.1660 0.1363 -0.0006 0.0000 -0.0212 -0.0491 0.406 - 26 16.3244 1.7470 0.7427 0.2111 0.0110 0.1472 0.1209 -0.0005 0.0000 -0.0197 -0.0444 0.413 - 27 16.6722 1.4928 0.4131 0.1691 0.0136 0.3781 0.1133 -0.0009 0.0000 -0.0161 -0.0208 0.392 - 28 16.9098 1.1466 0.2292 0.1263 0.0179 0.3678 0.1102 -0.0017 0.0000 -0.0101 -0.0176 0.342 - 29 17.0696 0.9138 0.1104 0.0787 0.0216 0.2876 0.0861 -0.0023 0.0000 -0.0029 -0.0114 0.284 - 30 17.1499 0.7967 0.0322 0.0268 0.0234 0.1122 0.0336 -0.0016 0.0000 0.0003 -0.0038 0.241 + 1 0.0114 7.7520 0.3539 1.8105 0.0503 0.3011 0.2335 0.1044 0.0000 -0.0160 -0.0606 0.318 + 2 0.1025 7.6885 1.0491 1.7378 0.0496 0.2914 0.2260 0.0209 0.0000 -0.0158 -0.0589 0.320 + 3 0.2837 7.5620 1.7073 1.7285 0.0483 0.2947 0.2286 0.0154 0.0000 -0.0151 -0.0589 0.316 + 4 0.5530 7.3741 2.3052 1.7160 0.0460 0.3000 0.2327 0.0135 0.0000 -0.0140 -0.0588 0.310 + 5 0.9075 7.1267 2.8223 1.6919 0.0427 0.3061 0.2374 0.0119 0.0000 -0.0128 -0.0588 0.304 + 6 1.3432 6.8226 3.2414 1.6510 0.0403 0.3120 0.2420 0.0103 0.0000 -0.0118 -0.0589 0.299 + 7 1.8554 6.4651 3.5491 1.5883 0.0423 0.3167 0.2457 0.0076 0.0000 -0.0112 -0.0592 0.296 + 8 2.4386 6.0582 3.7368 1.5019 0.0427 0.3196 0.2479 0.0058 0.0000 -0.0112 -0.0597 0.295 + 9 3.0862 5.6062 3.8005 1.3912 0.0343 0.3199 0.2482 0.0036 0.0000 -0.0121 -0.0604 0.299 + 10 3.7613 5.1351 3.4440 1.2643 0.0238 0.3174 0.2462 0.0019 0.0000 -0.0138 -0.0614 0.306 + 11 4.4532 4.6522 3.3149 1.1312 0.0131 0.3135 0.2432 -0.0002 0.0000 -0.0162 -0.0627 0.317 + 12 5.1831 4.1429 3.0930 0.9843 -0.0005 0.3063 0.2376 -0.0029 0.0000 -0.0198 -0.0646 0.333 + 13 6.0123 3.7903 3.4706 0.8530 -0.0074 0.2741 0.2251 -0.0034 0.0000 -0.0225 -0.0700 0.350 + 14 6.9353 3.6075 3.3775 0.7589 -0.0041 0.2562 0.2104 -0.0025 0.0000 -0.0231 -0.0672 0.360 + 15 7.8737 3.4215 3.2389 0.6821 -0.0018 0.2428 0.1994 -0.0020 0.0000 -0.0232 -0.0649 0.366 + 16 8.8172 3.2345 3.0619 0.6170 -0.0004 0.2323 0.1908 -0.0017 0.0000 -0.0232 -0.0630 0.371 + 17 9.7556 3.0486 2.8543 0.5605 0.0004 0.2239 0.1839 -0.0015 0.0000 -0.0231 -0.0614 0.376 + 18 10.6786 2.8657 2.6239 0.5107 0.0009 0.2170 0.1782 -0.0013 0.0000 -0.0230 -0.0600 0.379 + 19 11.5760 2.6879 2.3787 0.4661 0.0013 0.2112 0.1734 -0.0012 0.0000 -0.0229 -0.0589 0.382 + 20 12.4328 2.5181 2.1010 0.4259 0.0018 0.2060 0.1691 -0.0011 0.0000 -0.0227 -0.0578 0.384 + 21 13.2400 2.3582 1.8520 0.3890 0.0025 0.2009 0.1650 -0.0010 0.0000 -0.0225 -0.0566 0.386 + 22 13.9941 2.2087 1.6074 0.3544 0.0034 0.1954 0.1604 -0.0009 0.0000 -0.0221 -0.0553 0.388 + 23 14.6868 2.0715 1.3716 0.3207 0.0047 0.1885 0.1548 -0.0008 0.0000 -0.0215 -0.0535 0.389 + 24 15.3105 1.9479 1.1479 0.2866 0.0064 0.1792 0.1471 -0.0008 0.0000 -0.0205 -0.0509 0.390 + 25 15.8583 1.8393 0.9381 0.2504 0.0085 0.1658 0.1362 -0.0006 0.0000 -0.0192 -0.0473 0.391 + 26 16.3244 1.7470 0.7427 0.2104 0.0105 0.1467 0.1204 -0.0005 0.0000 -0.0177 -0.0425 0.397 + 27 16.6722 1.4928 0.4131 0.1684 0.0132 0.3766 0.1128 -0.0010 0.0000 -0.0145 -0.0200 0.379 + 28 16.9098 1.1466 0.2292 0.1260 0.0178 0.3668 0.1099 -0.0018 0.0000 -0.0088 -0.0170 0.330 + 29 17.0696 0.9138 0.1104 0.0786 0.0217 0.2872 0.0860 -0.0023 0.0000 -0.0021 -0.0110 0.274 + 30 17.1499 0.7967 0.0322 0.0268 0.0241 0.1123 0.0337 -0.0016 0.0000 0.0005 -0.0037 0.234 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.10754 Clsurf = 0.01779 - CYsurf = 0.00750 Cmsurf = -0.08937 - CDsurf = 0.00154 Cnsurf = -0.00082 - CDisurf = 0.00154 CDvsurf = 0.00000 + CLsurf = 0.10830 Clsurf = 0.01787 + CYsurf = 0.00751 Cmsurf = -0.08978 + CDsurf = 0.00153 Cnsurf = -0.00082 + CDisurf = 0.00153 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.21041 CDsurf = 0.00300 + CLsurf = 0.21190 CDsurf = 0.00298 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 1.7916 0.0504 0.2980 0.2311 0.1041 0.0000 -0.0144 0.0588 0.312 - 32 -0.1025 7.6885 1.0492 1.7205 0.0497 0.2885 0.2238 0.0209 0.0000 -0.0144 0.0573 0.314 - 33 -0.2837 7.5620 1.7073 1.7111 0.0481 0.2917 0.2263 0.0155 0.0000 -0.0137 0.0572 0.310 - 34 -0.5530 7.3741 2.3052 1.6983 0.0455 0.2969 0.2303 0.0135 0.0000 -0.0125 0.0571 0.304 - 35 -0.9075 7.1267 2.8223 1.6739 0.0421 0.3028 0.2349 0.0120 0.0000 -0.0113 0.0570 0.298 - 36 -1.3432 6.8226 3.2414 1.6333 0.0397 0.3086 0.2394 0.0102 0.0000 -0.0103 0.0572 0.293 - 37 -1.8554 6.4651 3.5491 1.5715 0.0416 0.3134 0.2431 0.0085 0.0000 -0.0098 0.0575 0.290 - 38 -2.4386 6.0582 3.7368 1.4858 0.0419 0.3162 0.2453 0.0059 0.0000 -0.0099 0.0581 0.291 - 39 -3.0862 5.6062 3.8005 1.3754 0.0332 0.3163 0.2453 0.0033 0.0000 -0.0110 0.0589 0.295 - 40 -3.7613 5.1351 3.4440 1.2501 0.0229 0.3139 0.2434 0.0016 0.0000 -0.0131 0.0603 0.304 - 41 -4.4532 4.6522 3.3149 1.1185 0.0132 0.3100 0.2404 -0.0005 0.0000 -0.0164 0.0624 0.318 - 42 -5.1831 4.1429 3.0930 0.9787 0.0003 0.3046 0.2362 -0.0027 0.0000 -0.0210 0.0652 0.339 - 43 -6.0123 3.7903 3.4706 0.8497 -0.0069 0.2730 0.2242 -0.0034 0.0000 -0.0242 0.0713 0.358 - 44 -6.9353 3.6075 3.3775 0.7562 -0.0038 0.2553 0.2096 -0.0025 0.0000 -0.0249 0.0687 0.369 - 45 -7.8737 3.4215 3.2389 0.6798 -0.0016 0.2420 0.1987 -0.0020 0.0000 -0.0251 0.0665 0.376 - 46 -8.8172 3.2345 3.0619 0.6151 -0.0003 0.2316 0.1902 -0.0017 0.0000 -0.0251 0.0646 0.382 - 47 -9.7556 3.0486 2.8543 0.5589 0.0005 0.2233 0.1833 -0.0015 0.0000 -0.0251 0.0630 0.387 - 48 -10.6786 2.8657 2.6240 0.5093 0.0009 0.2164 0.1777 -0.0013 0.0000 -0.0250 0.0617 0.391 - 49 -11.5760 2.6879 2.3787 0.4650 0.0013 0.2107 0.1730 -0.0012 0.0000 -0.0249 0.0606 0.394 - 50 -12.4328 2.5181 2.1010 0.4250 0.0018 0.2055 0.1688 -0.0011 0.0000 -0.0247 0.0595 0.397 - 51 -13.2400 2.3582 1.8520 0.3883 0.0025 0.2005 0.1647 -0.0010 0.0000 -0.0245 0.0584 0.399 - 52 -13.9941 2.2087 1.6074 0.3538 0.0034 0.1951 0.1602 -0.0009 0.0000 -0.0241 0.0570 0.401 - 53 -14.6868 2.0715 1.3716 0.3203 0.0048 0.1883 0.1546 -0.0008 0.0000 -0.0235 0.0553 0.402 - 54 -15.3105 1.9479 1.1479 0.2865 0.0065 0.1792 0.1471 -0.0007 0.0000 -0.0226 0.0527 0.403 - 55 -15.8583 1.8393 0.9381 0.2507 0.0086 0.1660 0.1363 -0.0006 0.0000 -0.0212 0.0491 0.406 - 56 -16.3244 1.7470 0.7427 0.2111 0.0110 0.1472 0.1209 -0.0005 0.0000 -0.0197 0.0444 0.413 - 57 -16.6722 1.4928 0.4131 0.1691 0.0136 0.3781 0.1133 -0.0009 0.0000 -0.0161 0.0208 0.392 - 58 -16.9098 1.1466 0.2292 0.1263 0.0179 0.3678 0.1102 -0.0017 0.0000 -0.0101 0.0176 0.342 - 59 -17.0696 0.9138 0.1104 0.0787 0.0216 0.2876 0.0861 -0.0023 0.0000 -0.0029 0.0114 0.284 - 60 -17.1499 0.7967 0.0322 0.0268 0.0234 0.1122 0.0336 -0.0016 0.0000 0.0003 0.0038 0.241 + 31 -0.0114 7.7520 0.3539 1.8105 0.0502 0.3011 0.2335 0.1044 0.0000 -0.0160 0.0606 0.318 + 32 -0.1025 7.6885 1.0491 1.7378 0.0496 0.2914 0.2260 0.0209 0.0000 -0.0158 0.0589 0.320 + 33 -0.2837 7.5620 1.7073 1.7285 0.0483 0.2947 0.2286 0.0154 0.0000 -0.0151 0.0589 0.316 + 34 -0.5530 7.3741 2.3052 1.7160 0.0460 0.3000 0.2327 0.0135 0.0000 -0.0140 0.0588 0.310 + 35 -0.9075 7.1267 2.8223 1.6919 0.0427 0.3061 0.2374 0.0119 0.0000 -0.0128 0.0588 0.304 + 36 -1.3432 6.8226 3.2414 1.6510 0.0403 0.3120 0.2420 0.0103 0.0000 -0.0118 0.0589 0.299 + 37 -1.8554 6.4651 3.5491 1.5883 0.0423 0.3167 0.2457 0.0076 0.0000 -0.0112 0.0592 0.296 + 38 -2.4386 6.0582 3.7368 1.5019 0.0427 0.3196 0.2479 0.0058 0.0000 -0.0112 0.0597 0.295 + 39 -3.0862 5.6062 3.8005 1.3912 0.0343 0.3199 0.2482 0.0036 0.0000 -0.0121 0.0604 0.299 + 40 -3.7613 5.1351 3.4440 1.2643 0.0238 0.3174 0.2462 0.0019 0.0000 -0.0138 0.0614 0.306 + 41 -4.4532 4.6522 3.3149 1.1312 0.0131 0.3135 0.2432 -0.0002 0.0000 -0.0162 0.0627 0.317 + 42 -5.1831 4.1429 3.0930 0.9843 -0.0005 0.3063 0.2376 -0.0029 0.0000 -0.0198 0.0646 0.333 + 43 -6.0123 3.7903 3.4706 0.8530 -0.0074 0.2741 0.2251 -0.0034 0.0000 -0.0225 0.0700 0.350 + 44 -6.9353 3.6075 3.3775 0.7589 -0.0041 0.2562 0.2104 -0.0025 0.0000 -0.0231 0.0672 0.360 + 45 -7.8737 3.4215 3.2389 0.6821 -0.0018 0.2428 0.1993 -0.0020 0.0000 -0.0232 0.0649 0.366 + 46 -8.8172 3.2345 3.0619 0.6170 -0.0004 0.2323 0.1908 -0.0017 0.0000 -0.0232 0.0630 0.371 + 47 -9.7556 3.0486 2.8543 0.5605 0.0004 0.2239 0.1839 -0.0015 0.0000 -0.0231 0.0614 0.376 + 48 -10.6786 2.8657 2.6239 0.5107 0.0009 0.2170 0.1782 -0.0013 0.0000 -0.0230 0.0600 0.379 + 49 -11.5760 2.6879 2.3787 0.4661 0.0013 0.2112 0.1734 -0.0012 0.0000 -0.0229 0.0589 0.382 + 50 -12.4328 2.5181 2.1010 0.4259 0.0018 0.2060 0.1691 -0.0011 0.0000 -0.0227 0.0578 0.384 + 51 -13.2400 2.3582 1.8520 0.3890 0.0025 0.2009 0.1650 -0.0010 0.0000 -0.0225 0.0566 0.386 + 52 -13.9941 2.2087 1.6074 0.3544 0.0034 0.1954 0.1604 -0.0009 0.0000 -0.0221 0.0553 0.388 + 53 -14.6868 2.0715 1.3716 0.3207 0.0047 0.1885 0.1548 -0.0008 0.0000 -0.0215 0.0535 0.389 + 54 -15.3105 1.9479 1.1479 0.2866 0.0064 0.1792 0.1471 -0.0008 0.0000 -0.0205 0.0509 0.390 + 55 -15.8583 1.8393 0.9381 0.2504 0.0085 0.1658 0.1362 -0.0006 0.0000 -0.0192 0.0473 0.391 + 56 -16.3244 1.7470 0.7427 0.2104 0.0105 0.1467 0.1204 -0.0005 0.0000 -0.0177 0.0425 0.397 + 57 -16.6722 1.4928 0.4131 0.1684 0.0132 0.3766 0.1128 -0.0010 0.0000 -0.0145 0.0200 0.379 + 58 -16.9098 1.1466 0.2292 0.1260 0.0178 0.3668 0.1099 -0.0018 0.0000 -0.0088 0.0170 0.330 + 59 -17.0696 0.9138 0.1104 0.0786 0.0217 0.2872 0.0860 -0.0023 0.0000 -0.0021 0.0110 0.274 + 60 -17.1499 0.7967 0.0322 0.0268 0.0241 0.1123 0.0337 -0.0016 0.0000 0.0005 0.0037 0.234 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01568 Clsurf = 0.00145 - CYsurf = 0.00252 Cmsurf = 0.07506 - CDsurf = -0.00022 Cnsurf = -0.00151 - CDisurf = -0.00022 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01586 Clsurf = 0.00147 + CYsurf = 0.00255 Cmsurf = 0.07593 + CDsurf = -0.00023 Cnsurf = -0.00153 + CDisurf = -0.00023 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.09557 CDsurf = -0.00135 + CLsurf = -0.09669 CDsurf = -0.00139 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.3594 0.0120 -0.1085 -0.0841 0.0217 0.0000 0.0051 0.0220 0.310 - 62 0.0418 4.2566 0.2392 -0.3921 0.0117 -0.1188 -0.0921 0.0010 0.0000 0.0049 0.0236 0.304 - 63 0.1156 4.2274 0.3930 -0.3946 0.0113 -0.1204 -0.0933 -0.0004 0.0000 0.0047 0.0236 0.300 - 64 0.2254 4.1839 0.5386 -0.3952 0.0109 -0.1218 -0.0945 -0.0007 0.0000 0.0042 0.0235 0.294 - 65 0.3698 4.1268 0.6730 -0.3952 0.0106 -0.1235 -0.0958 -0.0009 0.0000 0.0036 0.0232 0.287 - 66 0.5474 4.0565 0.7936 -0.3945 0.0102 -0.1254 -0.0973 -0.0011 0.0000 0.0028 0.0229 0.279 - 67 0.7617 3.9717 0.9441 -0.3929 0.0099 -0.1276 -0.0989 -0.0012 0.0000 0.0021 0.0227 0.271 - 68 1.0116 3.8728 1.0344 -0.3899 0.0098 -0.1299 -0.1007 -0.0014 0.0000 0.0014 0.0224 0.264 - 69 1.2891 3.7630 1.1046 -0.3855 0.0100 -0.1321 -0.1024 -0.0015 0.0000 0.0008 0.0223 0.258 - 70 1.5912 3.6435 1.1542 -0.3788 0.0103 -0.1341 -0.1040 -0.0017 0.0000 0.0003 0.0222 0.253 - 71 1.9146 3.5155 1.1831 -0.3698 0.0107 -0.1357 -0.1052 -0.0018 0.0000 -0.0002 0.0220 0.248 - 72 2.2558 3.3805 1.1921 -0.3584 0.0108 -0.1368 -0.1060 -0.0018 0.0000 -0.0005 0.0219 0.245 - 73 2.6109 3.2400 1.1821 -0.3443 0.0106 -0.1371 -0.1063 -0.0019 0.0000 -0.0008 0.0217 0.242 - 74 2.9762 3.0955 1.1548 -0.3279 0.0100 -0.1366 -0.1059 -0.0019 0.0000 -0.0010 0.0215 0.240 - 75 3.3476 2.9485 1.1122 -0.3094 0.0093 -0.1353 -0.1049 -0.0019 0.0000 -0.0012 0.0212 0.239 - 76 3.7210 2.8008 1.0564 -0.2892 0.0085 -0.1332 -0.1033 -0.0018 0.0000 -0.0013 0.0207 0.238 - 77 4.0924 2.6538 0.9900 -0.2680 0.0077 -0.1303 -0.1010 -0.0017 0.0000 -0.0013 0.0202 0.237 - 78 4.4577 2.5093 0.9155 -0.2462 0.0069 -0.1265 -0.0981 -0.0016 0.0000 -0.0014 0.0195 0.236 - 79 4.8128 2.3687 0.8353 -0.2244 0.0063 -0.1222 -0.0947 -0.0016 0.0000 -0.0015 0.0187 0.234 - 80 5.1540 2.2338 0.7518 -0.2030 0.0056 -0.1172 -0.0909 -0.0014 0.0000 -0.0017 0.0178 0.232 - 81 5.4774 2.1058 0.6671 -0.1821 0.0050 -0.1116 -0.0865 -0.0013 0.0000 -0.0019 0.0167 0.229 - 82 5.7795 1.9862 0.5830 -0.1621 0.0044 -0.1053 -0.0816 -0.0012 0.0000 -0.0022 0.0154 0.224 - 83 6.0570 1.8764 0.5012 -0.1428 0.0038 -0.0982 -0.0761 -0.0011 0.0000 -0.0025 0.0139 0.217 - 84 6.3069 1.7776 0.4225 -0.1243 0.0033 -0.0902 -0.0699 -0.0010 0.0000 -0.0030 0.0123 0.208 - 85 6.5264 1.6907 0.3478 -0.1063 0.0028 -0.0811 -0.0629 -0.0009 0.0000 -0.0034 0.0104 0.196 - 86 6.7314 1.6096 0.3326 -0.0877 0.0023 -0.0703 -0.0545 -0.0008 0.0000 -0.0037 0.0083 0.181 - 87 6.9144 1.5372 0.2507 -0.0682 0.0019 -0.0572 -0.0443 -0.0007 0.0000 -0.0038 0.0061 0.163 - 88 7.0535 1.4822 0.1746 -0.0487 0.0016 -0.0424 -0.0328 -0.0005 0.0000 -0.0035 0.0040 0.145 - 89 7.1471 1.4451 0.1029 -0.0292 0.0014 -0.0260 -0.0202 -0.0004 0.0000 -0.0024 0.0022 0.129 - 90 7.1941 1.4265 0.0340 -0.0097 0.0012 -0.0088 -0.0068 -0.0002 0.0000 -0.0009 0.0007 0.120 + 61 0.0047 4.2713 0.0803 -0.3635 0.0121 -0.1098 -0.0851 0.0223 0.0000 0.0051 0.0223 0.310 + 62 0.0418 4.2566 0.2392 -0.3970 0.0118 -0.1203 -0.0933 0.0010 0.0000 0.0050 0.0239 0.304 + 63 0.1156 4.2274 0.3930 -0.3997 0.0114 -0.1219 -0.0945 -0.0004 0.0000 0.0047 0.0240 0.300 + 64 0.2254 4.1839 0.5386 -0.4003 0.0110 -0.1234 -0.0957 -0.0008 0.0000 0.0042 0.0238 0.294 + 65 0.3698 4.1268 0.6730 -0.4002 0.0107 -0.1251 -0.0970 -0.0009 0.0000 0.0036 0.0235 0.287 + 66 0.5474 4.0565 0.7936 -0.3996 0.0103 -0.1271 -0.0985 -0.0011 0.0000 0.0029 0.0232 0.279 + 67 0.7617 3.9717 0.9441 -0.3979 0.0100 -0.1292 -0.1002 -0.0013 0.0000 0.0021 0.0229 0.271 + 68 1.0116 3.8728 1.0344 -0.3951 0.0099 -0.1316 -0.1020 -0.0014 0.0000 0.0014 0.0227 0.264 + 69 1.2891 3.7630 1.1046 -0.3905 0.0101 -0.1338 -0.1038 -0.0016 0.0000 0.0008 0.0226 0.258 + 70 1.5912 3.6435 1.1542 -0.3837 0.0105 -0.1358 -0.1053 -0.0017 0.0000 0.0003 0.0224 0.252 + 71 1.9146 3.5155 1.1831 -0.3746 0.0108 -0.1374 -0.1066 -0.0018 0.0000 -0.0002 0.0223 0.248 + 72 2.2558 3.3805 1.1921 -0.3630 0.0110 -0.1385 -0.1074 -0.0019 0.0000 -0.0006 0.0222 0.245 + 73 2.6109 3.2400 1.1821 -0.3486 0.0107 -0.1388 -0.1076 -0.0019 0.0000 -0.0008 0.0220 0.242 + 74 2.9762 3.0955 1.1548 -0.3318 0.0102 -0.1383 -0.1072 -0.0019 0.0000 -0.0010 0.0217 0.240 + 75 3.3476 2.9485 1.1122 -0.3130 0.0094 -0.1369 -0.1062 -0.0019 0.0000 -0.0012 0.0214 0.239 + 76 3.7210 2.8008 1.0564 -0.2925 0.0086 -0.1347 -0.1045 -0.0019 0.0000 -0.0013 0.0209 0.238 + 77 4.0924 2.6538 0.9900 -0.2709 0.0078 -0.1317 -0.1021 -0.0018 0.0000 -0.0014 0.0204 0.237 + 78 4.4577 2.5093 0.9155 -0.2488 0.0070 -0.1279 -0.0992 -0.0017 0.0000 -0.0014 0.0197 0.236 + 79 4.8128 2.3687 0.8353 -0.2266 0.0063 -0.1234 -0.0957 -0.0016 0.0000 -0.0015 0.0189 0.234 + 80 5.1540 2.2338 0.7518 -0.2049 0.0057 -0.1183 -0.0917 -0.0015 0.0000 -0.0017 0.0179 0.232 + 81 5.4774 2.1058 0.6671 -0.1838 0.0050 -0.1126 -0.0873 -0.0014 0.0000 -0.0019 0.0168 0.229 + 82 5.7795 1.9862 0.5830 -0.1635 0.0044 -0.1062 -0.0823 -0.0013 0.0000 -0.0022 0.0155 0.224 + 83 6.0570 1.8764 0.5012 -0.1440 0.0039 -0.0990 -0.0767 -0.0011 0.0000 -0.0025 0.0140 0.217 + 84 6.3069 1.7776 0.4225 -0.1252 0.0033 -0.0909 -0.0704 -0.0010 0.0000 -0.0030 0.0124 0.208 + 85 6.5264 1.6907 0.3478 -0.1070 0.0028 -0.0817 -0.0633 -0.0009 0.0000 -0.0034 0.0105 0.196 + 86 6.7314 1.6096 0.3326 -0.0884 0.0023 -0.0708 -0.0549 -0.0008 0.0000 -0.0038 0.0084 0.182 + 87 6.9144 1.5372 0.2507 -0.0686 0.0019 -0.0576 -0.0447 -0.0007 0.0000 -0.0039 0.0062 0.164 + 88 7.0535 1.4822 0.1746 -0.0490 0.0016 -0.0426 -0.0330 -0.0005 0.0000 -0.0035 0.0040 0.145 + 89 7.1471 1.4451 0.1029 -0.0294 0.0014 -0.0262 -0.0203 -0.0004 0.0000 -0.0025 0.0022 0.129 + 90 7.1941 1.4265 0.0340 -0.0098 0.0013 -0.0088 -0.0069 -0.0002 0.0000 -0.0009 0.0007 0.120 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.01568 Clsurf = -0.00145 - CYsurf = -0.00252 Cmsurf = 0.07506 - CDsurf = -0.00022 Cnsurf = 0.00151 - CDisurf = -0.00022 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.01586 Clsurf = -0.00147 + CYsurf = -0.00255 Cmsurf = 0.07593 + CDsurf = -0.00023 Cnsurf = 0.00153 + CDisurf = -0.00023 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.09557 CDsurf = -0.00135 + CLsurf = -0.09669 CDsurf = -0.00139 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.3594 0.0120 -0.1085 -0.0841 0.0217 0.0000 0.0051 -0.0220 0.310 - 92 -0.0418 4.2566 0.2392 -0.3921 0.0117 -0.1188 -0.0921 0.0010 0.0000 0.0049 -0.0236 0.304 - 93 -0.1156 4.2274 0.3930 -0.3946 0.0113 -0.1204 -0.0933 -0.0004 0.0000 0.0047 -0.0236 0.300 - 94 -0.2254 4.1839 0.5386 -0.3952 0.0109 -0.1218 -0.0945 -0.0007 0.0000 0.0042 -0.0235 0.294 - 95 -0.3698 4.1268 0.6730 -0.3952 0.0106 -0.1235 -0.0958 -0.0009 0.0000 0.0036 -0.0232 0.287 - 96 -0.5474 4.0565 0.7936 -0.3945 0.0102 -0.1254 -0.0973 -0.0011 0.0000 0.0028 -0.0229 0.279 - 97 -0.7617 3.9717 0.9441 -0.3929 0.0099 -0.1276 -0.0989 -0.0012 0.0000 0.0021 -0.0227 0.271 - 98 -1.0116 3.8728 1.0344 -0.3899 0.0098 -0.1299 -0.1007 -0.0014 0.0000 0.0014 -0.0224 0.264 - 99 -1.2891 3.7630 1.1046 -0.3854 0.0100 -0.1321 -0.1024 -0.0015 0.0000 0.0008 -0.0223 0.258 - 100 -1.5912 3.6435 1.1542 -0.3788 0.0103 -0.1341 -0.1040 -0.0017 0.0000 0.0003 -0.0222 0.253 - 101 -1.9146 3.5155 1.1831 -0.3698 0.0107 -0.1357 -0.1052 -0.0018 0.0000 -0.0002 -0.0220 0.248 - 102 -2.2558 3.3805 1.1921 -0.3584 0.0108 -0.1368 -0.1060 -0.0018 0.0000 -0.0005 -0.0219 0.245 - 103 -2.6109 3.2400 1.1821 -0.3443 0.0106 -0.1371 -0.1063 -0.0019 0.0000 -0.0008 -0.0217 0.242 - 104 -2.9762 3.0955 1.1548 -0.3279 0.0100 -0.1366 -0.1059 -0.0019 0.0000 -0.0010 -0.0215 0.240 - 105 -3.3476 2.9485 1.1122 -0.3094 0.0093 -0.1353 -0.1049 -0.0019 0.0000 -0.0012 -0.0212 0.239 - 106 -3.7210 2.8008 1.0564 -0.2892 0.0085 -0.1332 -0.1033 -0.0018 0.0000 -0.0013 -0.0207 0.238 - 107 -4.0924 2.6538 0.9900 -0.2680 0.0077 -0.1302 -0.1010 -0.0017 0.0000 -0.0013 -0.0202 0.237 - 108 -4.4577 2.5093 0.9155 -0.2462 0.0069 -0.1265 -0.0981 -0.0016 0.0000 -0.0014 -0.0195 0.236 - 109 -4.8128 2.3687 0.8353 -0.2244 0.0063 -0.1222 -0.0947 -0.0016 0.0000 -0.0015 -0.0187 0.234 - 110 -5.1540 2.2338 0.7518 -0.2030 0.0056 -0.1172 -0.0909 -0.0014 0.0000 -0.0017 -0.0178 0.232 - 111 -5.4774 2.1058 0.6671 -0.1821 0.0050 -0.1116 -0.0865 -0.0013 0.0000 -0.0019 -0.0167 0.229 - 112 -5.7795 1.9862 0.5830 -0.1621 0.0044 -0.1053 -0.0816 -0.0012 0.0000 -0.0022 -0.0154 0.224 - 113 -6.0570 1.8764 0.5012 -0.1428 0.0038 -0.0982 -0.0761 -0.0011 0.0000 -0.0025 -0.0139 0.217 - 114 -6.3069 1.7776 0.4225 -0.1243 0.0033 -0.0902 -0.0699 -0.0010 0.0000 -0.0030 -0.0123 0.208 - 115 -6.5264 1.6907 0.3478 -0.1063 0.0028 -0.0811 -0.0629 -0.0009 0.0000 -0.0034 -0.0104 0.196 - 116 -6.7314 1.6096 0.3326 -0.0877 0.0023 -0.0703 -0.0545 -0.0008 0.0000 -0.0037 -0.0083 0.181 - 117 -6.9144 1.5372 0.2507 -0.0682 0.0019 -0.0572 -0.0443 -0.0007 0.0000 -0.0038 -0.0061 0.163 - 118 -7.0535 1.4822 0.1746 -0.0487 0.0016 -0.0423 -0.0328 -0.0005 0.0000 -0.0035 -0.0040 0.145 - 119 -7.1471 1.4451 0.1029 -0.0292 0.0014 -0.0260 -0.0202 -0.0004 0.0000 -0.0024 -0.0022 0.129 - 120 -7.1941 1.4265 0.0340 -0.0097 0.0012 -0.0088 -0.0068 -0.0002 0.0000 -0.0009 -0.0007 0.120 + 91 -0.0047 4.2713 0.0803 -0.3635 0.0121 -0.1098 -0.0851 0.0223 0.0000 0.0051 -0.0223 0.310 + 92 -0.0418 4.2566 0.2392 -0.3970 0.0118 -0.1203 -0.0933 0.0010 0.0000 0.0050 -0.0239 0.304 + 93 -0.1156 4.2274 0.3930 -0.3997 0.0114 -0.1219 -0.0945 -0.0004 0.0000 0.0047 -0.0240 0.300 + 94 -0.2254 4.1839 0.5386 -0.4003 0.0110 -0.1234 -0.0957 -0.0008 0.0000 0.0042 -0.0238 0.294 + 95 -0.3698 4.1268 0.6730 -0.4002 0.0107 -0.1251 -0.0970 -0.0009 0.0000 0.0036 -0.0235 0.287 + 96 -0.5474 4.0565 0.7936 -0.3996 0.0103 -0.1271 -0.0985 -0.0011 0.0000 0.0029 -0.0232 0.279 + 97 -0.7617 3.9717 0.9441 -0.3979 0.0100 -0.1292 -0.1002 -0.0013 0.0000 0.0021 -0.0229 0.271 + 98 -1.0116 3.8728 1.0344 -0.3951 0.0099 -0.1316 -0.1020 -0.0014 0.0000 0.0014 -0.0227 0.264 + 99 -1.2891 3.7630 1.1046 -0.3905 0.0101 -0.1338 -0.1038 -0.0016 0.0000 0.0008 -0.0226 0.258 + 100 -1.5912 3.6435 1.1542 -0.3837 0.0105 -0.1358 -0.1053 -0.0017 0.0000 0.0003 -0.0224 0.252 + 101 -1.9146 3.5155 1.1831 -0.3746 0.0108 -0.1374 -0.1066 -0.0018 0.0000 -0.0002 -0.0223 0.248 + 102 -2.2558 3.3805 1.1921 -0.3630 0.0110 -0.1385 -0.1074 -0.0019 0.0000 -0.0006 -0.0222 0.245 + 103 -2.6109 3.2400 1.1821 -0.3486 0.0107 -0.1388 -0.1076 -0.0019 0.0000 -0.0008 -0.0220 0.242 + 104 -2.9762 3.0955 1.1548 -0.3318 0.0102 -0.1383 -0.1072 -0.0019 0.0000 -0.0010 -0.0217 0.240 + 105 -3.3476 2.9485 1.1122 -0.3130 0.0094 -0.1369 -0.1062 -0.0019 0.0000 -0.0012 -0.0214 0.239 + 106 -3.7210 2.8008 1.0564 -0.2925 0.0086 -0.1347 -0.1045 -0.0019 0.0000 -0.0013 -0.0209 0.238 + 107 -4.0924 2.6538 0.9900 -0.2709 0.0078 -0.1317 -0.1021 -0.0018 0.0000 -0.0014 -0.0204 0.237 + 108 -4.4577 2.5093 0.9155 -0.2488 0.0070 -0.1279 -0.0992 -0.0017 0.0000 -0.0014 -0.0197 0.236 + 109 -4.8128 2.3687 0.8353 -0.2266 0.0063 -0.1234 -0.0957 -0.0016 0.0000 -0.0015 -0.0189 0.234 + 110 -5.1540 2.2338 0.7518 -0.2049 0.0057 -0.1183 -0.0917 -0.0015 0.0000 -0.0017 -0.0179 0.232 + 111 -5.4774 2.1058 0.6671 -0.1838 0.0050 -0.1126 -0.0873 -0.0014 0.0000 -0.0019 -0.0168 0.229 + 112 -5.7795 1.9862 0.5830 -0.1635 0.0044 -0.1062 -0.0823 -0.0013 0.0000 -0.0022 -0.0155 0.224 + 113 -6.0570 1.8764 0.5012 -0.1440 0.0039 -0.0990 -0.0767 -0.0011 0.0000 -0.0025 -0.0140 0.217 + 114 -6.3069 1.7776 0.4225 -0.1252 0.0033 -0.0909 -0.0704 -0.0010 0.0000 -0.0030 -0.0124 0.208 + 115 -6.5264 1.6907 0.3478 -0.1070 0.0028 -0.0817 -0.0633 -0.0009 0.0000 -0.0034 -0.0105 0.196 + 116 -6.7314 1.6096 0.3326 -0.0884 0.0023 -0.0708 -0.0549 -0.0008 0.0000 -0.0038 -0.0084 0.182 + 117 -6.9144 1.5372 0.2507 -0.0686 0.0019 -0.0576 -0.0447 -0.0007 0.0000 -0.0039 -0.0062 0.164 + 118 -7.0535 1.4822 0.1746 -0.0490 0.0016 -0.0426 -0.0330 -0.0005 0.0000 -0.0035 -0.0040 0.145 + 119 -7.1471 1.4451 0.1029 -0.0294 0.0014 -0.0262 -0.0203 -0.0004 0.0000 -0.0025 -0.0022 0.129 + 120 -7.1941 1.4265 0.0340 -0.0098 0.0013 -0.0088 -0.0069 -0.0002 0.0000 -0.0009 -0.0007 0.120 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = -0.00000 CYsurf = -0.00000 Cmsurf = -0.00000 - CDsurf = 0.00000 Cnsurf = 0.00000 - CDisurf = 0.00000 CDvsurf = 0.00000 + CDsurf = -0.00000 Cnsurf = 0.00000 + CDisurf = -0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00000 CDsurf = 0.00000 + CLsurf = 0.00000 CDsurf = -0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.841 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.540 - 124 0.0000 9.1281 1.8040 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.355 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.224 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.128 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.044 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.958 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.865 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.763 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.690 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.648 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.610 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.572 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.534 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.499 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.473 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.440 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.421 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.399 - 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.363 - 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.339 - 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.313 - 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.319 - 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.305 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.276 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.263 - 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.244 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.227 - 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.220 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.743 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.481 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.322 + 127 0.0000 7.4000 2.2957 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.205 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.115 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.021 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.910 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.845 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.793 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.731 + 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.675 + 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.632 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.580 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.550 + 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.527 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.501 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.459 + 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.446 + 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.425 + 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.392 + 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.356 + 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.386 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.338 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.345 + 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.315 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.315 + 150 0.0000 1.1978 0.0252 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.349 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00511 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = -0.00510 - CDsurf = 0.00003 Cnsurf = -0.00000 + CLsurf = -0.00518 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00503 + CDsurf = 0.00003 Cnsurf = 0.00000 CDisurf = 0.00003 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00515 CDsurf = 0.00003 + CLsurf = -0.00522 CDsurf = 0.00003 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.1371 -0.0070 -0.0650 -0.0052 -0.0002 0.0000 0.0007 0.0003 0.393 - 152 -1.3090 31.2096 11.6724 -0.1782 -0.0014 -0.0223 -0.0057 -0.0000 0.0000 0.0006 0.0005 0.353 - 153 -0.9350 34.0626 12.7394 -0.1814 0.0155 -0.0130 -0.0053 0.0001 0.0000 0.0001 0.0005 0.274 - 154 -0.5610 36.1619 13.5246 -0.1790 0.0241 -0.0083 -0.0049 0.0001 0.0000 -0.0002 0.0005 0.218 - 155 -0.1870 37.5332 14.0374 -0.1772 0.0277 -0.0055 -0.0047 0.0001 0.0000 -0.0003 0.0006 0.191 - 156 0.1870 37.5332 14.0374 -0.1772 0.0277 -0.0055 -0.0047 0.0001 0.0000 -0.0003 0.0006 0.191 - 157 0.5610 36.1619 13.5246 -0.1790 0.0241 -0.0083 -0.0049 0.0001 0.0000 -0.0002 0.0005 0.218 - 158 0.9350 34.0626 12.7394 -0.1814 0.0155 -0.0130 -0.0053 0.0001 0.0000 0.0001 0.0005 0.274 - 159 1.3090 31.2096 11.6724 -0.1782 -0.0014 -0.0223 -0.0057 -0.0000 0.0000 0.0006 0.0005 0.353 - 160 1.6830 26.5957 9.9468 -0.1371 -0.0070 -0.0650 -0.0052 -0.0002 0.0000 0.0007 0.0003 0.393 + 151 -1.6830 26.5957 9.9468 -0.1390 -0.0070 -0.0659 -0.0052 -0.0002 0.0000 0.0008 0.0003 0.396 + 152 -1.3090 31.2096 11.6724 -0.1807 -0.0014 -0.0226 -0.0058 -0.0000 0.0000 0.0006 0.0005 0.356 + 153 -0.9350 34.0626 12.7394 -0.1840 0.0156 -0.0132 -0.0054 0.0001 0.0000 0.0001 0.0005 0.277 + 154 -0.5610 36.1619 13.5246 -0.1815 0.0243 -0.0084 -0.0050 0.0001 0.0000 -0.0001 0.0005 0.222 + 155 -0.1870 37.5332 14.0374 -0.1797 0.0280 -0.0056 -0.0048 0.0001 0.0000 -0.0003 0.0006 0.194 + 156 0.1870 37.5332 14.0374 -0.1797 0.0280 -0.0056 -0.0048 0.0001 0.0000 -0.0003 0.0006 0.194 + 157 0.5610 36.1619 13.5246 -0.1815 0.0243 -0.0084 -0.0050 0.0001 0.0000 -0.0001 0.0005 0.222 + 158 0.9350 34.0626 12.7394 -0.1840 0.0156 -0.0132 -0.0054 0.0001 0.0000 0.0001 0.0005 0.277 + 159 1.3090 31.2096 11.6724 -0.1807 -0.0014 -0.0226 -0.0058 -0.0000 0.0000 0.0006 0.0005 0.356 + 160 1.6830 26.5957 9.9468 -0.1390 -0.0070 -0.0659 -0.0052 -0.0002 0.0000 0.0008 0.0003 0.396 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.010 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.765 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.744 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.734 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.729 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.710 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.682 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.635 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.553 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.489 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.959 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.712 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.715 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.709 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.712 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.696 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.667 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.605 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.527 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.466 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_05_03.txt b/regression/scripts/AVL/avl_files/strip_forces_case_05_03.txt index de60b4cd22..0e9fe2ef35 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_05_03.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_05_03.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.20435 Clsurf = -0.03808 - CYsurf = -0.01397 Cmsurf = -0.18105 - CDsurf = 0.00413 Cnsurf = 0.00021 - CDisurf = 0.00413 CDvsurf = 0.00000 + CLsurf = 0.20515 Clsurf = -0.03816 + CYsurf = -0.01396 Cmsurf = -0.18148 + CDsurf = 0.00409 Cnsurf = 0.00021 + CDisurf = 0.00409 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39980 CDsurf = 0.00806 + CLsurf = 0.40136 CDsurf = 0.00798 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 2.8575 0.0880 0.4650 0.3602 0.2463 0.0000 -0.0237 -0.0946 0.316 - 2 0.1025 7.6885 1.0492 2.6870 0.0874 0.4493 0.3481 0.0469 0.0000 -0.0235 -0.0905 0.317 - 3 0.2837 7.5620 1.7073 2.6698 0.0859 0.4545 0.3521 0.0340 0.0000 -0.0223 -0.0903 0.313 - 4 0.5530 7.3741 2.3052 2.6542 0.0832 0.4636 0.3591 0.0300 0.0000 -0.0203 -0.0901 0.307 - 5 0.9075 7.1267 2.8223 2.6267 0.0791 0.4749 0.3678 0.0272 0.0000 -0.0182 -0.0901 0.299 - 6 1.3432 6.8226 3.2414 2.5819 0.0738 0.4878 0.3778 0.0238 0.0000 -0.0162 -0.0906 0.293 - 7 1.8554 6.4651 3.5491 2.5131 0.0680 0.5012 0.3882 0.0206 0.0000 -0.0148 -0.0915 0.288 - 8 2.4386 6.0582 3.7368 2.4168 0.0610 0.5146 0.3986 0.0155 0.0000 -0.0142 -0.0931 0.286 - 9 3.0862 5.6062 3.8005 2.2907 0.0510 0.5273 0.4085 0.0105 0.0000 -0.0147 -0.0955 0.286 - 10 3.7613 5.1351 3.4440 2.1450 0.0403 0.5393 0.4177 0.0072 0.0000 -0.0164 -0.0987 0.289 - 11 4.4532 4.6522 3.3149 1.9921 0.0293 0.5530 0.4284 0.0023 0.0000 -0.0193 -0.1032 0.295 - 12 5.1831 4.1429 3.0930 1.8261 0.0139 0.5695 0.4412 -0.0030 0.0000 -0.0232 -0.1090 0.303 - 13 6.0123 3.7903 3.4706 1.6644 0.0044 0.5369 0.4396 -0.0049 0.0000 -0.0247 -0.1200 0.306 - 14 6.9353 3.6075 3.3775 1.5435 0.0062 0.5230 0.4282 -0.0035 0.0000 -0.0251 -0.1178 0.309 - 15 7.8737 3.4215 3.2389 1.4387 0.0067 0.5140 0.4209 -0.0029 0.0000 -0.0251 -0.1162 0.310 - 16 8.8172 3.2345 3.0619 1.3441 0.0070 0.5080 0.4159 -0.0027 0.0000 -0.0250 -0.1150 0.310 - 17 9.7556 3.0486 2.8543 1.2562 0.0074 0.5037 0.4124 -0.0026 0.0000 -0.0248 -0.1140 0.310 - 18 10.6786 2.8657 2.6240 1.1733 0.0081 0.5005 0.4098 -0.0025 0.0000 -0.0246 -0.1132 0.310 - 19 11.5760 2.6879 2.3787 1.0942 0.0089 0.4976 0.4074 -0.0025 0.0000 -0.0243 -0.1125 0.310 - 20 12.4328 2.5181 2.1010 1.0182 0.0102 0.4943 0.4047 -0.0025 0.0000 -0.0238 -0.1114 0.309 - 21 13.2400 2.3582 1.8520 0.9440 0.0119 0.4894 0.4007 -0.0025 0.0000 -0.0232 -0.1100 0.308 - 22 13.9941 2.2087 1.6074 0.8700 0.0143 0.4815 0.3942 -0.0025 0.0000 -0.0221 -0.1076 0.306 - 23 14.6868 2.0715 1.3716 0.7939 0.0174 0.4685 0.3836 -0.0025 0.0000 -0.0205 -0.1038 0.304 - 24 15.3105 1.9479 1.1479 0.7128 0.0213 0.4474 0.3663 -0.0023 0.0000 -0.0183 -0.0980 0.300 - 25 15.8583 1.8393 0.9381 0.6233 0.0255 0.4142 0.3392 -0.0020 0.0000 -0.0160 -0.0898 0.297 - 26 16.3244 1.7470 0.7427 0.5228 0.0302 0.3658 0.2995 -0.0008 0.0000 -0.0157 -0.0807 0.302 - 27 16.6722 1.4928 0.4131 0.4157 0.0351 0.9378 0.2789 -0.0061 0.0000 -0.0141 -0.0397 0.300 - 28 16.9098 1.1466 0.2292 0.3072 0.0420 0.9030 0.2685 -0.0119 0.0000 -0.0013 -0.0326 0.255 - 29 17.0696 0.9138 0.1104 0.1894 0.0475 0.6995 0.2080 -0.0163 0.0000 0.0113 -0.0195 0.196 - 30 17.1499 0.7967 0.0322 0.0641 0.0501 0.2719 0.0808 -0.0112 0.0000 0.0086 -0.0056 0.144 + 1 0.0114 7.7520 0.3539 2.8773 0.0878 0.4683 0.3628 0.2471 0.0000 -0.0253 -0.0964 0.320 + 2 0.1025 7.6885 1.0491 2.7044 0.0873 0.4523 0.3503 0.0469 0.0000 -0.0249 -0.0922 0.321 + 3 0.2837 7.5620 1.7073 2.6872 0.0860 0.4575 0.3544 0.0340 0.0000 -0.0237 -0.0919 0.317 + 4 0.5530 7.3741 2.3052 2.6718 0.0836 0.4667 0.3615 0.0299 0.0000 -0.0218 -0.0918 0.310 + 5 0.9075 7.1267 2.8223 2.6447 0.0797 0.4781 0.3704 0.0267 0.0000 -0.0197 -0.0919 0.303 + 6 1.3432 6.8226 3.2414 2.5993 0.0744 0.4911 0.3804 0.0238 0.0000 -0.0177 -0.0923 0.297 + 7 1.8554 6.4651 3.5491 2.5288 0.0687 0.5044 0.3907 0.0183 0.0000 -0.0163 -0.0932 0.292 + 8 2.4386 6.0582 3.7368 2.4316 0.0618 0.5178 0.4011 0.0150 0.0000 -0.0156 -0.0947 0.289 + 9 3.0862 5.6062 3.8005 2.3060 0.0521 0.5308 0.4112 0.0111 0.0000 -0.0159 -0.0970 0.289 + 10 3.7613 5.1351 3.4440 2.1604 0.0412 0.5431 0.4207 0.0079 0.0000 -0.0171 -0.0999 0.291 + 11 4.4532 4.6522 3.3149 2.0106 0.0293 0.5581 0.4323 0.0033 0.0000 -0.0189 -0.1037 0.294 + 12 5.1831 4.1429 3.0930 1.8328 0.0131 0.5716 0.4428 -0.0033 0.0000 -0.0219 -0.1082 0.299 + 13 6.0123 3.7903 3.4706 1.6677 0.0039 0.5379 0.4404 -0.0049 0.0000 -0.0230 -0.1187 0.302 + 14 6.9353 3.6075 3.3775 1.5461 0.0059 0.5239 0.4290 -0.0035 0.0000 -0.0233 -0.1163 0.304 + 15 7.8737 3.4215 3.2389 1.4409 0.0065 0.5148 0.4215 -0.0029 0.0000 -0.0232 -0.1146 0.305 + 16 8.8172 3.2345 3.0619 1.3460 0.0068 0.5087 0.4165 -0.0027 0.0000 -0.0230 -0.1133 0.305 + 17 9.7556 3.0486 2.8543 1.2578 0.0073 0.5043 0.4129 -0.0026 0.0000 -0.0228 -0.1124 0.305 + 18 10.6786 2.8657 2.6239 1.1747 0.0080 0.5011 0.4102 -0.0025 0.0000 -0.0226 -0.1116 0.305 + 19 11.5760 2.6879 2.3787 1.0953 0.0089 0.4981 0.4078 -0.0025 0.0000 -0.0223 -0.1108 0.305 + 20 12.4328 2.5181 2.1010 1.0191 0.0101 0.4947 0.4050 -0.0025 0.0000 -0.0218 -0.1097 0.304 + 21 13.2400 2.3582 1.8520 0.9448 0.0119 0.4898 0.4010 -0.0025 0.0000 -0.0212 -0.1082 0.303 + 22 13.9941 2.2087 1.6074 0.8706 0.0142 0.4818 0.3945 -0.0026 0.0000 -0.0201 -0.1059 0.301 + 23 14.6868 2.0715 1.3716 0.7943 0.0174 0.4687 0.3838 -0.0025 0.0000 -0.0185 -0.1021 0.298 + 24 15.3105 1.9479 1.1479 0.7129 0.0212 0.4474 0.3663 -0.0024 0.0000 -0.0163 -0.0962 0.294 + 25 15.8583 1.8393 0.9381 0.6231 0.0255 0.4141 0.3390 -0.0020 0.0000 -0.0139 -0.0880 0.291 + 26 16.3244 1.7470 0.7427 0.5221 0.0298 0.3653 0.2991 -0.0009 0.0000 -0.0137 -0.0789 0.296 + 27 16.6722 1.4928 0.4131 0.4151 0.0347 0.9363 0.2784 -0.0062 0.0000 -0.0125 -0.0389 0.295 + 28 16.9098 1.1466 0.2292 0.3069 0.0419 0.9020 0.2682 -0.0120 0.0000 -0.0001 -0.0319 0.250 + 29 17.0696 0.9138 0.1104 0.1893 0.0476 0.6992 0.2079 -0.0164 0.0000 0.0121 -0.0191 0.192 + 30 17.1499 0.7967 0.0322 0.0641 0.0509 0.2721 0.0809 -0.0114 0.0000 0.0088 -0.0055 0.141 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.20435 Clsurf = 0.03808 - CYsurf = 0.01397 Cmsurf = -0.18105 - CDsurf = 0.00413 Cnsurf = -0.00021 - CDisurf = 0.00413 CDvsurf = 0.00000 + CLsurf = 0.20515 Clsurf = 0.03816 + CYsurf = 0.01396 Cmsurf = -0.18148 + CDsurf = 0.00409 Cnsurf = -0.00021 + CDisurf = 0.00409 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.39980 CDsurf = 0.00806 + CLsurf = 0.40136 CDsurf = 0.00798 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 2.8575 0.0880 0.4650 0.3602 0.2463 0.0000 -0.0237 0.0946 0.316 - 32 -0.1025 7.6885 1.0492 2.6870 0.0874 0.4493 0.3481 0.0469 0.0000 -0.0235 0.0905 0.317 - 33 -0.2837 7.5620 1.7073 2.6698 0.0859 0.4545 0.3521 0.0340 0.0000 -0.0223 0.0903 0.313 - 34 -0.5530 7.3741 2.3052 2.6542 0.0832 0.4636 0.3591 0.0300 0.0000 -0.0203 0.0901 0.307 - 35 -0.9075 7.1267 2.8223 2.6267 0.0791 0.4749 0.3678 0.0272 0.0000 -0.0182 0.0901 0.299 - 36 -1.3432 6.8226 3.2414 2.5819 0.0738 0.4878 0.3778 0.0238 0.0000 -0.0162 0.0906 0.293 - 37 -1.8554 6.4651 3.5491 2.5130 0.0680 0.5012 0.3882 0.0206 0.0000 -0.0148 0.0915 0.288 - 38 -2.4386 6.0582 3.7368 2.4168 0.0610 0.5146 0.3986 0.0155 0.0000 -0.0142 0.0931 0.286 - 39 -3.0862 5.6062 3.8005 2.2907 0.0510 0.5273 0.4085 0.0105 0.0000 -0.0147 0.0955 0.286 - 40 -3.7613 5.1351 3.4440 2.1450 0.0403 0.5393 0.4177 0.0072 0.0000 -0.0164 0.0987 0.289 - 41 -4.4532 4.6522 3.3149 1.9920 0.0293 0.5530 0.4284 0.0023 0.0000 -0.0193 0.1032 0.295 - 42 -5.1831 4.1429 3.0930 1.8261 0.0139 0.5695 0.4411 -0.0030 0.0000 -0.0232 0.1089 0.303 - 43 -6.0123 3.7903 3.4706 1.6644 0.0044 0.5369 0.4396 -0.0049 0.0000 -0.0247 0.1200 0.306 - 44 -6.9353 3.6075 3.3775 1.5434 0.0062 0.5230 0.4282 -0.0035 0.0000 -0.0251 0.1178 0.309 - 45 -7.8737 3.4215 3.2389 1.4387 0.0067 0.5140 0.4208 -0.0029 0.0000 -0.0251 0.1162 0.310 - 46 -8.8172 3.2345 3.0619 1.3441 0.0070 0.5080 0.4159 -0.0027 0.0000 -0.0250 0.1150 0.310 - 47 -9.7556 3.0486 2.8543 1.2562 0.0074 0.5037 0.4124 -0.0026 0.0000 -0.0248 0.1140 0.310 - 48 -10.6786 2.8657 2.6240 1.1733 0.0081 0.5005 0.4098 -0.0025 0.0000 -0.0246 0.1132 0.310 - 49 -11.5760 2.6879 2.3787 1.0942 0.0089 0.4976 0.4074 -0.0025 0.0000 -0.0243 0.1125 0.310 - 50 -12.4328 2.5181 2.1010 1.0181 0.0102 0.4943 0.4047 -0.0025 0.0000 -0.0238 0.1114 0.309 - 51 -13.2400 2.3582 1.8520 0.9440 0.0119 0.4894 0.4007 -0.0025 0.0000 -0.0232 0.1100 0.308 - 52 -13.9941 2.2087 1.6074 0.8700 0.0143 0.4815 0.3942 -0.0025 0.0000 -0.0221 0.1076 0.306 - 53 -14.6868 2.0715 1.3716 0.7939 0.0174 0.4685 0.3836 -0.0025 0.0000 -0.0205 0.1038 0.304 - 54 -15.3105 1.9479 1.1479 0.7128 0.0213 0.4473 0.3663 -0.0023 0.0000 -0.0183 0.0980 0.300 - 55 -15.8583 1.8393 0.9381 0.6233 0.0255 0.4142 0.3391 -0.0020 0.0000 -0.0160 0.0898 0.297 - 56 -16.3244 1.7470 0.7427 0.5228 0.0302 0.3658 0.2995 -0.0008 0.0000 -0.0157 0.0807 0.302 - 57 -16.6722 1.4928 0.4131 0.4157 0.0351 0.9378 0.2789 -0.0061 0.0000 -0.0141 0.0397 0.300 - 58 -16.9098 1.1466 0.2292 0.3072 0.0420 0.9030 0.2685 -0.0119 0.0000 -0.0013 0.0326 0.255 - 59 -17.0696 0.9138 0.1104 0.1894 0.0475 0.6995 0.2080 -0.0163 0.0000 0.0113 0.0195 0.196 - 60 -17.1499 0.7967 0.0322 0.0641 0.0501 0.2719 0.0808 -0.0112 0.0000 0.0086 0.0056 0.144 + 31 -0.0114 7.7520 0.3539 2.8773 0.0878 0.4683 0.3628 0.2471 0.0000 -0.0253 0.0964 0.320 + 32 -0.1025 7.6885 1.0491 2.7044 0.0873 0.4523 0.3503 0.0469 0.0000 -0.0249 0.0922 0.321 + 33 -0.2837 7.5620 1.7073 2.6872 0.0860 0.4575 0.3544 0.0340 0.0000 -0.0237 0.0919 0.317 + 34 -0.5530 7.3741 2.3052 2.6718 0.0836 0.4667 0.3615 0.0299 0.0000 -0.0218 0.0918 0.310 + 35 -0.9075 7.1267 2.8223 2.6447 0.0797 0.4781 0.3704 0.0267 0.0000 -0.0197 0.0919 0.303 + 36 -1.3432 6.8226 3.2414 2.5993 0.0744 0.4911 0.3804 0.0238 0.0000 -0.0177 0.0923 0.297 + 37 -1.8554 6.4651 3.5491 2.5288 0.0687 0.5044 0.3907 0.0183 0.0000 -0.0163 0.0932 0.292 + 38 -2.4386 6.0582 3.7368 2.4316 0.0618 0.5178 0.4011 0.0150 0.0000 -0.0156 0.0947 0.289 + 39 -3.0862 5.6062 3.8005 2.3060 0.0521 0.5308 0.4112 0.0111 0.0000 -0.0159 0.0970 0.289 + 40 -3.7613 5.1351 3.4440 2.1604 0.0412 0.5431 0.4207 0.0079 0.0000 -0.0171 0.0999 0.291 + 41 -4.4532 4.6522 3.3149 2.0106 0.0293 0.5581 0.4323 0.0033 0.0000 -0.0189 0.1037 0.294 + 42 -5.1831 4.1429 3.0930 1.8328 0.0131 0.5716 0.4428 -0.0033 0.0000 -0.0219 0.1082 0.299 + 43 -6.0123 3.7903 3.4706 1.6677 0.0039 0.5379 0.4404 -0.0049 0.0000 -0.0230 0.1187 0.302 + 44 -6.9353 3.6075 3.3775 1.5460 0.0059 0.5239 0.4290 -0.0035 0.0000 -0.0233 0.1163 0.304 + 45 -7.8737 3.4215 3.2389 1.4409 0.0065 0.5148 0.4215 -0.0029 0.0000 -0.0232 0.1146 0.305 + 46 -8.8172 3.2345 3.0619 1.3460 0.0068 0.5087 0.4165 -0.0027 0.0000 -0.0230 0.1133 0.305 + 47 -9.7556 3.0486 2.8543 1.2578 0.0073 0.5043 0.4129 -0.0026 0.0000 -0.0228 0.1124 0.305 + 48 -10.6786 2.8657 2.6239 1.1747 0.0080 0.5011 0.4102 -0.0025 0.0000 -0.0226 0.1116 0.305 + 49 -11.5760 2.6879 2.3787 1.0953 0.0089 0.4981 0.4078 -0.0025 0.0000 -0.0223 0.1108 0.305 + 50 -12.4328 2.5181 2.1010 1.0191 0.0101 0.4947 0.4050 -0.0025 0.0000 -0.0218 0.1097 0.304 + 51 -13.2400 2.3582 1.8520 0.9448 0.0119 0.4898 0.4010 -0.0025 0.0000 -0.0212 0.1082 0.303 + 52 -13.9941 2.2087 1.6074 0.8706 0.0142 0.4818 0.3945 -0.0026 0.0000 -0.0201 0.1059 0.301 + 53 -14.6868 2.0715 1.3716 0.7943 0.0174 0.4687 0.3838 -0.0025 0.0000 -0.0185 0.1021 0.298 + 54 -15.3105 1.9479 1.1479 0.7129 0.0212 0.4474 0.3663 -0.0024 0.0000 -0.0163 0.0962 0.294 + 55 -15.8583 1.8393 0.9381 0.6231 0.0255 0.4141 0.3390 -0.0020 0.0000 -0.0139 0.0880 0.291 + 56 -16.3244 1.7470 0.7427 0.5221 0.0298 0.3653 0.2991 -0.0009 0.0000 -0.0137 0.0789 0.296 + 57 -16.6722 1.4928 0.4131 0.4151 0.0347 0.9363 0.2784 -0.0062 0.0000 -0.0125 0.0389 0.295 + 58 -16.9098 1.1466 0.2292 0.3069 0.0419 0.9020 0.2682 -0.0120 0.0000 -0.0001 0.0319 0.250 + 59 -17.0696 0.9138 0.1104 0.1893 0.0476 0.6992 0.2079 -0.0164 0.0000 0.0121 0.0191 0.192 + 60 -17.1499 0.7967 0.0322 0.0641 0.0509 0.2721 0.0809 -0.0114 0.0000 0.0088 0.0055 0.141 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00135 Clsurf = -0.00029 - CYsurf = -0.00021 Cmsurf = -0.00731 - CDsurf = 0.00003 Cnsurf = 0.00014 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00117 Clsurf = -0.00027 + CYsurf = -0.00018 Cmsurf = -0.00645 + CDsurf = 0.00003 Cnsurf = 0.00012 CDisurf = 0.00003 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00825 CDsurf = 0.00021 + CLsurf = 0.00715 CDsurf = 0.00017 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.0299 0.0458 -0.0091 -0.0070 -0.0000 0.0000 -0.0008 0.0008 0.138 - 62 0.0418 4.2566 0.2392 -0.0302 0.0457 -0.0092 -0.0071 -0.0002 0.0000 -0.0008 0.0008 0.136 - 63 0.1156 4.2274 0.3930 -0.0301 0.0454 -0.0092 -0.0071 -0.0003 0.0000 -0.0008 0.0008 0.132 - 64 0.2254 4.1839 0.5386 -0.0300 0.0450 -0.0093 -0.0072 -0.0003 0.0000 -0.0009 0.0008 0.125 - 65 0.3698 4.1268 0.6730 -0.0298 0.0444 -0.0093 -0.0072 -0.0003 0.0000 -0.0010 0.0007 0.115 - 66 0.5474 4.0565 0.7936 -0.0292 0.0435 -0.0093 -0.0072 -0.0003 0.0000 -0.0011 0.0006 0.104 - 67 0.7617 3.9717 0.9441 -0.0283 0.0424 -0.0092 -0.0071 -0.0003 0.0000 -0.0011 0.0006 0.089 - 68 1.0116 3.8728 1.0344 -0.0267 0.0410 -0.0089 -0.0069 -0.0003 0.0000 -0.0012 0.0004 0.070 - 69 1.2891 3.7630 1.1046 -0.0243 0.0395 -0.0084 -0.0065 -0.0002 0.0000 -0.0013 0.0003 0.044 - 70 1.5912 3.6435 1.1542 -0.0207 0.0380 -0.0074 -0.0057 -0.0002 0.0000 -0.0014 0.0000 0.002 - 71 1.9146 3.5155 1.1831 -0.0157 0.0364 -0.0058 -0.0045 -0.0002 0.0000 -0.0015 -0.0003 -0.078 - 72 2.2558 3.3805 1.1921 -0.0092 0.0349 -0.0035 -0.0027 -0.0001 0.0000 -0.0015 -0.0007 -0.297 - 73 2.6109 3.2400 1.1821 -0.0012 0.0334 -0.0005 -0.0004 -0.0000 0.0000 -0.0015 -0.0012 - 74 2.9762 3.0955 1.1548 0.0083 0.0321 0.0035 0.0027 0.0001 0.0000 -0.0014 -0.0018 0.782 - 75 3.3476 2.9485 1.1122 0.0188 0.0309 0.0083 0.0064 0.0002 0.0000 -0.0013 -0.0025 0.457 - 76 3.7210 2.8008 1.0564 0.0299 0.0299 0.0138 0.0107 0.0004 0.0000 -0.0012 -0.0032 0.359 - 77 4.0924 2.6538 0.9900 0.0410 0.0291 0.0200 0.0154 0.0005 0.0000 -0.0010 -0.0041 0.312 - 78 4.4577 2.5093 0.9155 0.0514 0.0285 0.0266 0.0205 0.0007 0.0000 -0.0007 -0.0050 0.284 - 79 4.8128 2.3687 0.8353 0.0607 0.0281 0.0332 0.0256 0.0008 0.0000 -0.0004 -0.0058 0.265 - 80 5.1540 2.2338 0.7518 0.0684 0.0279 0.0397 0.0306 0.0009 0.0000 0.0000 -0.0065 0.250 - 81 5.4774 2.1058 0.6671 0.0738 0.0279 0.0455 0.0350 0.0010 0.0000 0.0005 -0.0071 0.237 - 82 5.7795 1.9862 0.5830 0.0769 0.0281 0.0502 0.0387 0.0011 0.0000 0.0010 -0.0074 0.225 - 83 6.0570 1.8764 0.5012 0.0774 0.0284 0.0535 0.0412 0.0011 0.0000 0.0016 -0.0075 0.211 - 84 6.3069 1.7776 0.4225 0.0753 0.0287 0.0549 0.0423 0.0011 0.0000 0.0022 -0.0071 0.197 - 85 6.5264 1.6907 0.3478 0.0706 0.0290 0.0541 0.0418 0.0010 0.0000 0.0029 -0.0065 0.181 - 86 6.7314 1.6096 0.3326 0.0632 0.0293 0.0509 0.0393 0.0009 0.0000 0.0034 -0.0055 0.162 - 87 6.9144 1.5372 0.2507 0.0525 0.0296 0.0443 0.0341 0.0007 0.0000 0.0037 -0.0041 0.141 - 88 7.0535 1.4822 0.1746 0.0393 0.0299 0.0344 0.0265 0.0005 0.0000 0.0035 -0.0027 0.120 - 89 7.1471 1.4451 0.1029 0.0243 0.0301 0.0218 0.0168 0.0003 0.0000 0.0025 -0.0015 0.102 - 90 7.1941 1.4265 0.0340 0.0082 0.0302 0.0075 0.0058 0.0000 0.0000 0.0009 -0.0005 0.092 + 61 0.0047 4.2713 0.0803 -0.0349 0.0459 -0.0106 -0.0082 -0.0000 0.0000 -0.0007 0.0011 0.161 + 62 0.0418 4.2566 0.2392 -0.0353 0.0458 -0.0107 -0.0083 -0.0003 0.0000 -0.0007 0.0011 0.160 + 63 0.1156 4.2274 0.3930 -0.0352 0.0455 -0.0108 -0.0083 -0.0003 0.0000 -0.0008 0.0011 0.156 + 64 0.2254 4.1839 0.5386 -0.0351 0.0451 -0.0109 -0.0084 -0.0003 0.0000 -0.0008 0.0011 0.149 + 65 0.3698 4.1268 0.6730 -0.0348 0.0445 -0.0109 -0.0084 -0.0003 0.0000 -0.0009 0.0010 0.140 + 66 0.5474 4.0565 0.7936 -0.0343 0.0436 -0.0110 -0.0084 -0.0003 0.0000 -0.0010 0.0009 0.129 + 67 0.7617 3.9717 0.9441 -0.0333 0.0425 -0.0109 -0.0084 -0.0003 0.0000 -0.0011 0.0008 0.116 + 68 1.0116 3.8728 1.0344 -0.0317 0.0412 -0.0106 -0.0082 -0.0003 0.0000 -0.0012 0.0007 0.100 + 69 1.2891 3.7630 1.1046 -0.0292 0.0396 -0.0101 -0.0078 -0.0003 0.0000 -0.0013 0.0005 0.079 + 70 1.5912 3.6435 1.1542 -0.0255 0.0381 -0.0091 -0.0070 -0.0003 0.0000 -0.0014 0.0003 0.048 + 71 1.9146 3.5155 1.1831 -0.0204 0.0365 -0.0075 -0.0058 -0.0002 0.0000 -0.0015 -0.0000 -0.005 + 72 2.2558 3.3805 1.1921 -0.0137 0.0350 -0.0053 -0.0040 -0.0002 0.0000 -0.0015 -0.0004 -0.123 + 73 2.6109 3.2400 1.1821 -0.0054 0.0335 -0.0022 -0.0017 -0.0001 0.0000 -0.0015 -0.0009 -0.653 + 74 2.9762 3.0955 1.1548 0.0043 0.0322 0.0018 0.0014 0.0000 0.0000 -0.0014 -0.0015 1.281 + 75 3.3476 2.9485 1.1122 0.0152 0.0310 0.0067 0.0051 0.0002 0.0000 -0.0013 -0.0022 0.511 + 76 3.7210 2.8008 1.0564 0.0266 0.0300 0.0123 0.0095 0.0003 0.0000 -0.0012 -0.0030 0.375 + 77 4.0924 2.6538 0.9900 0.0381 0.0292 0.0186 0.0143 0.0005 0.0000 -0.0010 -0.0039 0.318 + 78 4.4577 2.5093 0.9155 0.0489 0.0286 0.0253 0.0195 0.0006 0.0000 -0.0007 -0.0048 0.287 + 79 4.8128 2.3687 0.8353 0.0586 0.0282 0.0320 0.0247 0.0008 0.0000 -0.0004 -0.0056 0.266 + 80 5.1540 2.2338 0.7518 0.0665 0.0280 0.0386 0.0297 0.0009 0.0000 -0.0000 -0.0064 0.250 + 81 5.4774 2.1058 0.6671 0.0723 0.0280 0.0445 0.0343 0.0010 0.0000 0.0004 -0.0069 0.237 + 82 5.7795 1.9862 0.5830 0.0756 0.0281 0.0493 0.0380 0.0011 0.0000 0.0010 -0.0073 0.225 + 83 6.0570 1.8764 0.5012 0.0763 0.0284 0.0527 0.0406 0.0011 0.0000 0.0016 -0.0073 0.211 + 84 6.3069 1.7776 0.4225 0.0744 0.0287 0.0542 0.0418 0.0011 0.0000 0.0022 -0.0070 0.197 + 85 6.5264 1.6907 0.3478 0.0699 0.0290 0.0536 0.0413 0.0010 0.0000 0.0029 -0.0064 0.181 + 86 6.7314 1.6096 0.3326 0.0626 0.0294 0.0505 0.0389 0.0009 0.0000 0.0034 -0.0054 0.162 + 87 6.9144 1.5372 0.2507 0.0520 0.0297 0.0439 0.0339 0.0007 0.0000 0.0037 -0.0041 0.141 + 88 7.0535 1.4822 0.1746 0.0390 0.0299 0.0341 0.0263 0.0005 0.0000 0.0034 -0.0027 0.119 + 89 7.1471 1.4451 0.1029 0.0241 0.0301 0.0217 0.0167 0.0003 0.0000 0.0025 -0.0015 0.102 + 90 7.1941 1.4265 0.0340 0.0082 0.0302 0.0074 0.0057 0.0000 0.0000 0.0009 -0.0005 0.092 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.00135 Clsurf = 0.00029 - CYsurf = 0.00021 Cmsurf = -0.00731 - CDsurf = 0.00003 Cnsurf = -0.00014 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.00117 Clsurf = 0.00027 + CYsurf = 0.00018 Cmsurf = -0.00645 + CDsurf = 0.00003 Cnsurf = -0.00012 CDisurf = 0.00003 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00825 CDsurf = 0.00021 + CLsurf = 0.00715 CDsurf = 0.00017 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.0299 0.0458 -0.0091 -0.0070 -0.0000 0.0000 -0.0008 -0.0008 0.138 - 92 -0.0418 4.2566 0.2392 -0.0302 0.0457 -0.0092 -0.0071 -0.0002 0.0000 -0.0008 -0.0008 0.136 - 93 -0.1156 4.2274 0.3930 -0.0301 0.0454 -0.0092 -0.0071 -0.0003 0.0000 -0.0008 -0.0008 0.132 - 94 -0.2254 4.1839 0.5386 -0.0300 0.0450 -0.0093 -0.0072 -0.0003 0.0000 -0.0009 -0.0008 0.125 - 95 -0.3698 4.1268 0.6730 -0.0298 0.0444 -0.0093 -0.0072 -0.0003 0.0000 -0.0010 -0.0007 0.115 - 96 -0.5474 4.0565 0.7936 -0.0292 0.0435 -0.0093 -0.0072 -0.0003 0.0000 -0.0011 -0.0006 0.104 - 97 -0.7617 3.9717 0.9441 -0.0283 0.0424 -0.0092 -0.0071 -0.0003 0.0000 -0.0011 -0.0006 0.089 - 98 -1.0116 3.8728 1.0344 -0.0267 0.0410 -0.0089 -0.0069 -0.0003 0.0000 -0.0012 -0.0004 0.070 - 99 -1.2891 3.7630 1.1046 -0.0243 0.0395 -0.0084 -0.0065 -0.0002 0.0000 -0.0013 -0.0003 0.044 - 100 -1.5912 3.6435 1.1542 -0.0207 0.0380 -0.0074 -0.0057 -0.0002 0.0000 -0.0014 -0.0000 0.002 - 101 -1.9146 3.5155 1.1831 -0.0157 0.0364 -0.0058 -0.0045 -0.0002 0.0000 -0.0015 0.0003 -0.078 - 102 -2.2558 3.3805 1.1921 -0.0092 0.0349 -0.0035 -0.0027 -0.0001 0.0000 -0.0015 0.0007 -0.297 - 103 -2.6109 3.2400 1.1821 -0.0012 0.0334 -0.0005 -0.0004 -0.0000 0.0000 -0.0015 0.0012 - 104 -2.9762 3.0955 1.1548 0.0083 0.0321 0.0035 0.0027 0.0001 0.0000 -0.0014 0.0018 0.781 - 105 -3.3476 2.9485 1.1122 0.0188 0.0309 0.0083 0.0064 0.0002 0.0000 -0.0013 0.0025 0.457 - 106 -3.7210 2.8008 1.0564 0.0299 0.0299 0.0138 0.0107 0.0004 0.0000 -0.0012 0.0032 0.359 - 107 -4.0924 2.6538 0.9900 0.0410 0.0291 0.0200 0.0154 0.0005 0.0000 -0.0010 0.0041 0.312 - 108 -4.4577 2.5093 0.9155 0.0514 0.0285 0.0266 0.0205 0.0007 0.0000 -0.0007 0.0050 0.284 - 109 -4.8128 2.3687 0.8353 0.0607 0.0281 0.0332 0.0256 0.0008 0.0000 -0.0004 0.0058 0.265 - 110 -5.1540 2.2338 0.7518 0.0684 0.0279 0.0397 0.0306 0.0009 0.0000 0.0000 0.0065 0.250 - 111 -5.4774 2.1058 0.6671 0.0738 0.0279 0.0455 0.0350 0.0010 0.0000 0.0005 0.0071 0.237 - 112 -5.7795 1.9862 0.5830 0.0769 0.0281 0.0502 0.0387 0.0011 0.0000 0.0010 0.0074 0.225 - 113 -6.0570 1.8764 0.5012 0.0774 0.0284 0.0535 0.0412 0.0011 0.0000 0.0016 0.0075 0.211 - 114 -6.3069 1.7776 0.4225 0.0753 0.0287 0.0549 0.0423 0.0011 0.0000 0.0022 0.0071 0.197 - 115 -6.5264 1.6907 0.3478 0.0706 0.0290 0.0541 0.0418 0.0010 0.0000 0.0029 0.0065 0.181 - 116 -6.7314 1.6096 0.3326 0.0632 0.0293 0.0509 0.0393 0.0009 0.0000 0.0034 0.0055 0.162 - 117 -6.9144 1.5372 0.2507 0.0525 0.0296 0.0443 0.0341 0.0007 0.0000 0.0037 0.0041 0.141 - 118 -7.0535 1.4822 0.1746 0.0393 0.0299 0.0344 0.0265 0.0005 0.0000 0.0035 0.0027 0.120 - 119 -7.1471 1.4451 0.1029 0.0243 0.0301 0.0218 0.0168 0.0003 0.0000 0.0025 0.0015 0.102 - 120 -7.1941 1.4265 0.0340 0.0082 0.0302 0.0075 0.0058 0.0000 0.0000 0.0009 0.0005 0.092 + 91 -0.0047 4.2713 0.0803 -0.0349 0.0459 -0.0106 -0.0082 -0.0000 0.0000 -0.0007 -0.0011 0.161 + 92 -0.0418 4.2566 0.2392 -0.0353 0.0458 -0.0107 -0.0083 -0.0003 0.0000 -0.0007 -0.0011 0.160 + 93 -0.1156 4.2274 0.3930 -0.0352 0.0455 -0.0108 -0.0083 -0.0003 0.0000 -0.0008 -0.0011 0.156 + 94 -0.2254 4.1839 0.5386 -0.0351 0.0451 -0.0109 -0.0084 -0.0003 0.0000 -0.0008 -0.0011 0.149 + 95 -0.3698 4.1268 0.6730 -0.0348 0.0445 -0.0109 -0.0084 -0.0003 0.0000 -0.0009 -0.0010 0.140 + 96 -0.5474 4.0565 0.7936 -0.0343 0.0436 -0.0110 -0.0084 -0.0003 0.0000 -0.0010 -0.0009 0.129 + 97 -0.7617 3.9717 0.9441 -0.0333 0.0425 -0.0109 -0.0084 -0.0003 0.0000 -0.0011 -0.0008 0.116 + 98 -1.0116 3.8728 1.0344 -0.0317 0.0412 -0.0106 -0.0082 -0.0003 0.0000 -0.0012 -0.0007 0.100 + 99 -1.2891 3.7630 1.1046 -0.0292 0.0396 -0.0101 -0.0078 -0.0003 0.0000 -0.0013 -0.0005 0.079 + 100 -1.5912 3.6435 1.1542 -0.0255 0.0381 -0.0091 -0.0070 -0.0003 0.0000 -0.0014 -0.0003 0.048 + 101 -1.9146 3.5155 1.1831 -0.0204 0.0365 -0.0075 -0.0058 -0.0002 0.0000 -0.0015 0.0000 -0.005 + 102 -2.2558 3.3805 1.1921 -0.0137 0.0350 -0.0053 -0.0040 -0.0002 0.0000 -0.0015 0.0004 -0.123 + 103 -2.6109 3.2400 1.1821 -0.0054 0.0335 -0.0022 -0.0017 -0.0001 0.0000 -0.0015 0.0009 -0.653 + 104 -2.9762 3.0955 1.1548 0.0043 0.0322 0.0018 0.0014 0.0000 0.0000 -0.0014 0.0015 1.281 + 105 -3.3476 2.9485 1.1122 0.0152 0.0310 0.0067 0.0051 0.0002 0.0000 -0.0013 0.0022 0.511 + 106 -3.7210 2.8008 1.0564 0.0266 0.0300 0.0123 0.0095 0.0003 0.0000 -0.0012 0.0030 0.375 + 107 -4.0924 2.6538 0.9900 0.0381 0.0292 0.0186 0.0143 0.0005 0.0000 -0.0010 0.0039 0.318 + 108 -4.4577 2.5093 0.9155 0.0489 0.0286 0.0253 0.0195 0.0006 0.0000 -0.0007 0.0048 0.287 + 109 -4.8128 2.3687 0.8353 0.0586 0.0282 0.0320 0.0247 0.0008 0.0000 -0.0004 0.0056 0.266 + 110 -5.1540 2.2338 0.7518 0.0665 0.0280 0.0386 0.0297 0.0009 0.0000 -0.0000 0.0064 0.250 + 111 -5.4774 2.1058 0.6671 0.0723 0.0280 0.0445 0.0343 0.0010 0.0000 0.0004 0.0069 0.237 + 112 -5.7795 1.9862 0.5830 0.0756 0.0281 0.0493 0.0380 0.0011 0.0000 0.0010 0.0073 0.225 + 113 -6.0570 1.8764 0.5012 0.0763 0.0284 0.0527 0.0406 0.0011 0.0000 0.0016 0.0073 0.211 + 114 -6.3069 1.7776 0.4225 0.0744 0.0287 0.0542 0.0418 0.0011 0.0000 0.0022 0.0070 0.197 + 115 -6.5264 1.6907 0.3478 0.0699 0.0290 0.0536 0.0413 0.0010 0.0000 0.0029 0.0064 0.181 + 116 -6.7314 1.6096 0.3326 0.0626 0.0294 0.0505 0.0389 0.0009 0.0000 0.0034 0.0054 0.162 + 117 -6.9144 1.5372 0.2507 0.0520 0.0297 0.0439 0.0339 0.0007 0.0000 0.0037 0.0041 0.141 + 118 -7.0535 1.4822 0.1746 0.0390 0.0299 0.0341 0.0263 0.0005 0.0000 0.0034 0.0027 0.119 + 119 -7.1471 1.4451 0.1029 0.0241 0.0301 0.0217 0.0167 0.0003 0.0000 0.0025 0.0015 0.102 + 120 -7.1941 1.4265 0.0340 0.0082 0.0302 0.0074 0.0057 0.0000 0.0000 0.0009 0.0005 0.092 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.193 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.192 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.189 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.190 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.187 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.190 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.205 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.210 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.191 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.193 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.206 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.214 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.248 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.253 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.252 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.248 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 + 129 0.0000 5.8609 2.1733 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.190 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.195 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.211 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.223 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.201 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.190 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.175 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.152 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.130 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.103 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.208 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.188 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.177 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.154 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.134 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.116 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.101 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00059 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.01493 + CLsurf = -0.00066 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.01500 CDsurf = -0.00010 Cnsurf = -0.00000 CDisurf = -0.00010 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00059 CDsurf = -0.00010 + CLsurf = -0.00067 CDsurf = -0.00010 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.0285 0.0484 -0.0130 -0.0010 -0.0007 0.0000 0.0018 0.0003 1.993 - 152 -1.3090 31.2096 11.6724 -0.0272 0.0567 -0.0034 -0.0009 -0.0002 0.0000 0.0020 0.0006 - 153 -0.9350 34.0626 12.7394 -0.0201 0.0638 -0.0014 -0.0006 -0.0000 0.0000 0.0020 0.0007 - 154 -0.5610 36.1619 13.5246 -0.0135 0.0687 -0.0006 -0.0004 0.0001 0.0000 0.0020 0.0009 - 155 -0.1870 37.5332 14.0374 -0.0095 0.0715 -0.0003 -0.0003 0.0002 0.0000 0.0020 0.0014 - 156 0.1870 37.5332 14.0374 -0.0095 0.0715 -0.0003 -0.0003 0.0002 0.0000 0.0020 0.0014 - 157 0.5610 36.1619 13.5246 -0.0135 0.0687 -0.0006 -0.0004 0.0001 0.0000 0.0020 0.0009 - 158 0.9350 34.0626 12.7394 -0.0201 0.0639 -0.0014 -0.0006 -0.0000 0.0000 0.0020 0.0007 - 159 1.3090 31.2096 11.6724 -0.0272 0.0567 -0.0034 -0.0009 -0.0002 0.0000 0.0020 0.0006 - 160 1.6830 26.5957 9.9468 -0.0285 0.0484 -0.0130 -0.0010 -0.0007 0.0000 0.0018 0.0003 1.993 + 151 -1.6830 26.5957 9.9468 -0.0304 0.0483 -0.0139 -0.0011 -0.0007 0.0000 0.0019 0.0003 1.903 + 152 -1.3090 31.2096 11.6724 -0.0297 0.0567 -0.0037 -0.0009 -0.0002 0.0000 0.0020 0.0006 + 153 -0.9350 34.0626 12.7394 -0.0227 0.0640 -0.0016 -0.0007 -0.0000 0.0000 0.0021 0.0007 + 154 -0.5610 36.1619 13.5246 -0.0160 0.0689 -0.0007 -0.0004 0.0001 0.0000 0.0020 0.0010 + 155 -0.1870 37.5332 14.0374 -0.0120 0.0717 -0.0004 -0.0003 0.0002 0.0000 0.0020 0.0014 + 156 0.1870 37.5332 14.0374 -0.0120 0.0717 -0.0004 -0.0003 0.0002 0.0000 0.0020 0.0014 + 157 0.5610 36.1619 13.5246 -0.0160 0.0689 -0.0007 -0.0004 0.0001 0.0000 0.0020 0.0010 + 158 0.9350 34.0626 12.7394 -0.0227 0.0640 -0.0016 -0.0007 -0.0000 0.0000 0.0021 0.0007 + 159 1.3090 31.2096 11.6724 -0.0297 0.0567 -0.0037 -0.0009 -0.0002 0.0000 0.0020 0.0006 + 160 1.6830 26.5957 9.9468 -0.0304 0.0483 -0.0139 -0.0011 -0.0007 0.0000 0.0019 0.0003 1.903 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = -0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = -0.00000 Cnsurf = -0.00000 - CDisurf = -0.00000 CDvsurf = 0.00000 + CDsurf = 0.00000 Cnsurf = -0.00000 + CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = 0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.540 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.513 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.513 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.525 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.555 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.559 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.561 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.562 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.593 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 1.142 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.403 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.443 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.459 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.492 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.530 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.537 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.533 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.539 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.572 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_05_04.txt b/regression/scripts/AVL/avl_files/strip_forces_case_05_04.txt index 0ac7bb5962..fcb555acb2 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_05_04.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_05_04.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.34881 Clsurf = -0.06815 - CYsurf = -0.02163 Cmsurf = -0.31770 - CDsurf = 0.01078 Cnsurf = -0.00375 - CDisurf = 0.01078 CDvsurf = 0.00000 + CLsurf = 0.34969 Clsurf = -0.06825 + CYsurf = -0.02156 Cmsurf = -0.31816 + CDsurf = 0.01066 Cnsurf = -0.00376 + CDisurf = 0.01066 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.68214 CDsurf = 0.02105 + CLsurf = 0.68385 CDsurf = 0.02081 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 4.5316 0.1441 0.6932 0.5367 0.5722 0.0000 -0.0376 -0.1506 0.320 - 2 0.1025 7.6885 1.0492 4.1310 0.1437 0.6849 0.5302 0.1047 0.0000 -0.0370 -0.1404 0.320 - 3 0.2837 7.5620 1.7073 4.0959 0.1423 0.6939 0.5372 0.0747 0.0000 -0.0351 -0.1398 0.315 - 4 0.5530 7.3741 2.3052 4.0748 0.1395 0.7090 0.5489 0.0663 0.0000 -0.0320 -0.1395 0.308 - 5 0.9075 7.1267 2.8223 4.0421 0.1344 0.7286 0.5640 0.0609 0.0000 -0.0284 -0.1396 0.300 - 6 1.3432 6.8226 3.2414 3.9912 0.1248 0.7524 0.5825 0.0544 0.0000 -0.0250 -0.1405 0.293 - 7 1.8554 6.4651 3.5491 3.9120 0.1074 0.7791 0.6032 0.0484 0.0000 -0.0223 -0.1424 0.287 - 8 2.4386 6.0582 3.7368 3.8003 0.0896 0.8091 0.6263 0.0384 0.0000 -0.0206 -0.1456 0.283 - 9 3.0862 5.6062 3.8005 3.6507 0.0775 0.8411 0.6512 0.0285 0.0000 -0.0202 -0.1502 0.281 - 10 3.7613 5.1351 3.4440 3.4743 0.0662 0.8748 0.6772 0.0227 0.0000 -0.0212 -0.1562 0.281 - 11 4.4532 4.6522 3.3149 3.2917 0.0535 0.9161 0.7092 0.0122 0.0000 -0.0235 -0.1644 0.283 - 12 5.1831 4.1429 3.0930 3.0889 0.0342 0.9668 0.7484 0.0008 0.0000 -0.0262 -0.1744 0.285 - 13 6.0123 3.7903 3.4706 2.8743 0.0213 0.9333 0.7616 -0.0040 0.0000 -0.0247 -0.1925 0.282 - 14 6.9353 3.6075 3.3775 2.7116 0.0211 0.9249 0.7547 -0.0021 0.0000 -0.0246 -0.1909 0.283 - 15 7.8737 3.4215 3.2389 2.5646 0.0191 0.9223 0.7526 -0.0020 0.0000 -0.0243 -0.1902 0.282 - 16 8.8172 3.2345 3.0619 2.4256 0.0178 0.9228 0.7530 -0.0023 0.0000 -0.0239 -0.1899 0.282 - 17 9.7556 3.0486 2.8543 2.2906 0.0178 0.9246 0.7545 -0.0029 0.0000 -0.0235 -0.1899 0.281 - 18 10.6786 2.8657 2.6240 2.1582 0.0187 0.9268 0.7563 -0.0034 0.0000 -0.0231 -0.1899 0.281 - 19 11.5760 2.6879 2.3787 2.0275 0.0203 0.9283 0.7575 -0.0041 0.0000 -0.0225 -0.1897 0.280 - 20 12.4328 2.5181 2.1010 1.8980 0.0227 0.9277 0.7570 -0.0047 0.0000 -0.0217 -0.1888 0.279 - 21 13.2400 2.3582 1.8520 1.7684 0.0260 0.9230 0.7532 -0.0053 0.0000 -0.0204 -0.1868 0.277 - 22 13.9941 2.2087 1.6074 1.6357 0.0305 0.9116 0.7439 -0.0058 0.0000 -0.0184 -0.1829 0.275 - 23 14.6868 2.0715 1.3716 1.4963 0.0364 0.8893 0.7256 -0.0061 0.0000 -0.0153 -0.1761 0.271 - 24 15.3105 1.9479 1.1479 1.3451 0.0434 0.8501 0.6937 -0.0062 0.0000 -0.0112 -0.1653 0.266 - 25 15.8583 1.8393 0.9381 1.1759 0.0510 0.7870 0.6422 -0.0053 0.0000 -0.0074 -0.1505 0.262 - 26 16.3244 1.7470 0.7427 0.9851 0.0589 0.6937 0.5661 -0.0009 0.0000 -0.0090 -0.1348 0.266 - 27 16.6722 1.4928 0.4131 0.7812 0.0673 1.7740 0.5274 -0.0229 0.0000 -0.0103 -0.0689 0.269 - 28 16.9098 1.1466 0.2292 0.5753 0.0781 1.7076 0.5076 -0.0446 0.0000 0.0125 -0.0558 0.225 - 29 17.0696 0.9138 0.1104 0.3535 0.0862 1.3248 0.3938 -0.0616 0.0000 0.0330 -0.0323 0.166 - 30 17.1499 0.7967 0.0322 0.1193 0.0901 0.5191 0.1543 -0.0450 0.0000 0.0211 -0.0087 0.113 + 1 0.0114 7.7520 0.3539 4.5527 0.1440 0.6966 0.5393 0.5737 0.0000 -0.0394 -0.1525 0.323 + 2 0.1025 7.6885 1.0491 4.1484 0.1436 0.6878 0.5325 0.1047 0.0000 -0.0384 -0.1420 0.322 + 3 0.2837 7.5620 1.7073 4.1132 0.1425 0.6968 0.5395 0.0747 0.0000 -0.0365 -0.1414 0.318 + 4 0.5530 7.3741 2.3052 4.0921 0.1399 0.7121 0.5513 0.0659 0.0000 -0.0334 -0.1412 0.311 + 5 0.9075 7.1267 2.8223 4.0598 0.1350 0.7319 0.5666 0.0598 0.0000 -0.0299 -0.1413 0.303 + 6 1.3432 6.8226 3.2414 4.0078 0.1254 0.7556 0.5849 0.0541 0.0000 -0.0265 -0.1422 0.295 + 7 1.8554 6.4651 3.5491 3.9253 0.1081 0.7824 0.6057 0.0429 0.0000 -0.0238 -0.1440 0.289 + 8 2.4386 6.0582 3.7368 3.8123 0.0904 0.8118 0.6284 0.0369 0.0000 -0.0220 -0.1471 0.285 + 9 3.0862 5.6062 3.8005 3.6648 0.0787 0.8443 0.6536 0.0297 0.0000 -0.0214 -0.1516 0.283 + 10 3.7613 5.1351 3.4440 3.4925 0.0671 0.8792 0.6806 0.0240 0.0000 -0.0220 -0.1575 0.282 + 11 4.4532 4.6522 3.3149 3.3239 0.0534 0.9248 0.7159 0.0149 0.0000 -0.0226 -0.1651 0.282 + 12 5.1831 4.1429 3.0930 3.0981 0.0334 0.9697 0.7507 0.0001 0.0000 -0.0247 -0.1736 0.283 + 13 6.0123 3.7903 3.4706 2.8775 0.0208 0.9343 0.7624 -0.0039 0.0000 -0.0230 -0.1912 0.280 + 14 6.9353 3.6075 3.3775 2.7139 0.0208 0.9257 0.7554 -0.0021 0.0000 -0.0227 -0.1894 0.280 + 15 7.8737 3.4215 3.2389 2.5666 0.0189 0.9230 0.7531 -0.0019 0.0000 -0.0223 -0.1886 0.280 + 16 8.8172 3.2345 3.0619 2.4275 0.0177 0.9235 0.7536 -0.0023 0.0000 -0.0220 -0.1883 0.279 + 17 9.7556 3.0486 2.8543 2.2922 0.0177 0.9252 0.7550 -0.0030 0.0000 -0.0216 -0.1883 0.279 + 18 10.6786 2.8657 2.6239 2.1596 0.0186 0.9274 0.7568 -0.0035 0.0000 -0.0211 -0.1883 0.278 + 19 11.5760 2.6879 2.3787 2.0286 0.0203 0.9289 0.7580 -0.0041 0.0000 -0.0205 -0.1880 0.277 + 20 12.4328 2.5181 2.1010 1.8990 0.0226 0.9282 0.7574 -0.0048 0.0000 -0.0197 -0.1871 0.276 + 21 13.2400 2.3582 1.8520 1.7691 0.0259 0.9235 0.7535 -0.0054 0.0000 -0.0184 -0.1851 0.274 + 22 13.9941 2.2087 1.6074 1.6364 0.0304 0.9120 0.7442 -0.0059 0.0000 -0.0163 -0.1812 0.272 + 23 14.6868 2.0715 1.3716 1.4967 0.0363 0.8895 0.7258 -0.0062 0.0000 -0.0133 -0.1744 0.268 + 24 15.3105 1.9479 1.1479 1.3452 0.0433 0.8502 0.6938 -0.0063 0.0000 -0.0092 -0.1636 0.263 + 25 15.8583 1.8393 0.9381 1.1758 0.0509 0.7869 0.6422 -0.0054 0.0000 -0.0054 -0.1487 0.258 + 26 16.3244 1.7470 0.7427 0.9844 0.0585 0.6933 0.5657 -0.0011 0.0000 -0.0070 -0.1330 0.262 + 27 16.6722 1.4928 0.4131 0.7806 0.0669 1.7727 0.5270 -0.0232 0.0000 -0.0087 -0.0681 0.266 + 28 16.9098 1.1466 0.2292 0.5750 0.0780 1.7067 0.5074 -0.0448 0.0000 0.0138 -0.0552 0.223 + 29 17.0696 0.9138 0.1104 0.3534 0.0863 1.3246 0.3937 -0.0619 0.0000 0.0339 -0.0319 0.164 + 30 17.1499 0.7967 0.0322 0.1194 0.0909 0.5194 0.1544 -0.0454 0.0000 0.0214 -0.0086 0.112 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.34881 Clsurf = 0.06815 - CYsurf = 0.02163 Cmsurf = -0.31770 - CDsurf = 0.01078 Cnsurf = 0.00375 - CDisurf = 0.01078 CDvsurf = 0.00000 + CLsurf = 0.34969 Clsurf = 0.06825 + CYsurf = 0.02156 Cmsurf = -0.31816 + CDsurf = 0.01066 Cnsurf = 0.00376 + CDisurf = 0.01066 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.68213 CDsurf = 0.02105 + CLsurf = 0.68384 CDsurf = 0.02081 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 4.5316 0.1442 0.6932 0.5367 0.5723 0.0000 -0.0376 0.1506 0.320 - 32 -0.1025 7.6885 1.0492 4.1310 0.1437 0.6849 0.5302 0.1047 0.0000 -0.0370 0.1404 0.320 - 33 -0.2837 7.5620 1.7073 4.0959 0.1423 0.6939 0.5372 0.0747 0.0000 -0.0351 0.1398 0.315 - 34 -0.5530 7.3741 2.3052 4.0748 0.1395 0.7090 0.5489 0.0663 0.0000 -0.0320 0.1395 0.308 - 35 -0.9075 7.1267 2.8223 4.0421 0.1344 0.7286 0.5640 0.0609 0.0000 -0.0284 0.1396 0.300 - 36 -1.3432 6.8226 3.2414 3.9912 0.1248 0.7524 0.5825 0.0544 0.0000 -0.0250 0.1405 0.293 - 37 -1.8554 6.4651 3.5491 3.9120 0.1074 0.7791 0.6032 0.0484 0.0000 -0.0223 0.1424 0.287 - 38 -2.4386 6.0582 3.7368 3.8003 0.0896 0.8091 0.6263 0.0384 0.0000 -0.0206 0.1456 0.283 - 39 -3.0862 5.6062 3.8005 3.6507 0.0775 0.8411 0.6512 0.0285 0.0000 -0.0202 0.1502 0.281 - 40 -3.7613 5.1351 3.4440 3.4743 0.0662 0.8748 0.6772 0.0227 0.0000 -0.0212 0.1562 0.281 - 41 -4.4532 4.6522 3.3149 3.2916 0.0535 0.9161 0.7092 0.0122 0.0000 -0.0235 0.1644 0.283 - 42 -5.1831 4.1429 3.0930 3.0889 0.0342 0.9668 0.7484 0.0008 0.0000 -0.0262 0.1744 0.285 - 43 -6.0123 3.7903 3.4706 2.8743 0.0213 0.9333 0.7616 -0.0040 0.0000 -0.0247 0.1925 0.282 - 44 -6.9353 3.6075 3.3775 2.7116 0.0211 0.9249 0.7547 -0.0021 0.0000 -0.0246 0.1909 0.283 - 45 -7.8737 3.4215 3.2389 2.5646 0.0191 0.9223 0.7526 -0.0020 0.0000 -0.0243 0.1902 0.282 - 46 -8.8172 3.2345 3.0619 2.4256 0.0178 0.9227 0.7530 -0.0023 0.0000 -0.0239 0.1899 0.282 - 47 -9.7556 3.0486 2.8543 2.2905 0.0178 0.9246 0.7545 -0.0029 0.0000 -0.0235 0.1899 0.281 - 48 -10.6786 2.8657 2.6240 2.1582 0.0187 0.9268 0.7563 -0.0034 0.0000 -0.0231 0.1899 0.281 - 49 -11.5760 2.6879 2.3787 2.0275 0.0203 0.9283 0.7575 -0.0041 0.0000 -0.0225 0.1897 0.280 - 50 -12.4328 2.5181 2.1010 1.8980 0.0227 0.9277 0.7570 -0.0047 0.0000 -0.0217 0.1888 0.279 - 51 -13.2400 2.3582 1.8520 1.7683 0.0260 0.9230 0.7532 -0.0053 0.0000 -0.0204 0.1868 0.277 - 52 -13.9941 2.2087 1.6074 1.6357 0.0305 0.9116 0.7439 -0.0058 0.0000 -0.0184 0.1829 0.275 - 53 -14.6868 2.0715 1.3716 1.4963 0.0364 0.8892 0.7256 -0.0061 0.0000 -0.0153 0.1761 0.271 - 54 -15.3105 1.9479 1.1479 1.3451 0.0434 0.8501 0.6937 -0.0062 0.0000 -0.0112 0.1653 0.266 - 55 -15.8583 1.8393 0.9381 1.1759 0.0510 0.7870 0.6422 -0.0053 0.0000 -0.0074 0.1504 0.262 - 56 -16.3244 1.7470 0.7427 0.9851 0.0589 0.6937 0.5661 -0.0009 0.0000 -0.0090 0.1348 0.266 - 57 -16.6722 1.4928 0.4131 0.7812 0.0673 1.7740 0.5274 -0.0229 0.0000 -0.0103 0.0689 0.269 - 58 -16.9098 1.1466 0.2292 0.5753 0.0781 1.7076 0.5076 -0.0446 0.0000 0.0125 0.0558 0.225 - 59 -17.0696 0.9138 0.1104 0.3535 0.0862 1.3248 0.3938 -0.0616 0.0000 0.0330 0.0323 0.166 - 60 -17.1499 0.7967 0.0322 0.1193 0.0901 0.5191 0.1543 -0.0450 0.0000 0.0211 0.0087 0.113 + 31 -0.0114 7.7520 0.3539 4.5527 0.1440 0.6966 0.5393 0.5737 0.0000 -0.0394 0.1525 0.323 + 32 -0.1025 7.6885 1.0491 4.1484 0.1436 0.6878 0.5325 0.1047 0.0000 -0.0384 0.1420 0.322 + 33 -0.2837 7.5620 1.7073 4.1132 0.1425 0.6968 0.5395 0.0747 0.0000 -0.0365 0.1414 0.318 + 34 -0.5530 7.3741 2.3052 4.0921 0.1399 0.7121 0.5513 0.0659 0.0000 -0.0334 0.1412 0.311 + 35 -0.9075 7.1267 2.8223 4.0598 0.1350 0.7319 0.5666 0.0598 0.0000 -0.0299 0.1413 0.303 + 36 -1.3432 6.8226 3.2414 4.0078 0.1254 0.7556 0.5849 0.0541 0.0000 -0.0265 0.1422 0.295 + 37 -1.8554 6.4651 3.5491 3.9253 0.1081 0.7824 0.6057 0.0429 0.0000 -0.0238 0.1440 0.289 + 38 -2.4386 6.0582 3.7368 3.8123 0.0904 0.8118 0.6284 0.0369 0.0000 -0.0220 0.1471 0.285 + 39 -3.0862 5.6062 3.8005 3.6647 0.0787 0.8443 0.6536 0.0297 0.0000 -0.0214 0.1516 0.283 + 40 -3.7613 5.1351 3.4440 3.4925 0.0671 0.8792 0.6806 0.0240 0.0000 -0.0220 0.1575 0.282 + 41 -4.4532 4.6522 3.3149 3.3238 0.0534 0.9248 0.7159 0.0149 0.0000 -0.0226 0.1651 0.282 + 42 -5.1831 4.1429 3.0930 3.0981 0.0334 0.9697 0.7507 0.0001 0.0000 -0.0247 0.1736 0.283 + 43 -6.0123 3.7903 3.4706 2.8775 0.0208 0.9343 0.7624 -0.0039 0.0000 -0.0230 0.1912 0.280 + 44 -6.9353 3.6075 3.3775 2.7139 0.0208 0.9257 0.7554 -0.0021 0.0000 -0.0227 0.1894 0.280 + 45 -7.8737 3.4215 3.2389 2.5666 0.0189 0.9230 0.7531 -0.0019 0.0000 -0.0223 0.1886 0.280 + 46 -8.8172 3.2345 3.0619 2.4275 0.0177 0.9235 0.7536 -0.0023 0.0000 -0.0220 0.1883 0.279 + 47 -9.7556 3.0486 2.8543 2.2922 0.0177 0.9252 0.7550 -0.0030 0.0000 -0.0216 0.1883 0.279 + 48 -10.6786 2.8657 2.6239 2.1596 0.0186 0.9274 0.7568 -0.0035 0.0000 -0.0211 0.1883 0.278 + 49 -11.5760 2.6879 2.3787 2.0286 0.0203 0.9289 0.7580 -0.0041 0.0000 -0.0205 0.1880 0.277 + 50 -12.4328 2.5181 2.1010 1.8990 0.0226 0.9282 0.7574 -0.0048 0.0000 -0.0197 0.1871 0.276 + 51 -13.2400 2.3582 1.8520 1.7691 0.0259 0.9234 0.7535 -0.0054 0.0000 -0.0184 0.1851 0.274 + 52 -13.9941 2.2087 1.6074 1.6364 0.0304 0.9120 0.7442 -0.0059 0.0000 -0.0163 0.1812 0.272 + 53 -14.6868 2.0715 1.3716 1.4967 0.0363 0.8895 0.7258 -0.0062 0.0000 -0.0133 0.1744 0.268 + 54 -15.3105 1.9479 1.1479 1.3452 0.0433 0.8502 0.6938 -0.0063 0.0000 -0.0092 0.1636 0.263 + 55 -15.8583 1.8393 0.9381 1.1758 0.0509 0.7869 0.6422 -0.0054 0.0000 -0.0054 0.1487 0.258 + 56 -16.3244 1.7470 0.7427 0.9844 0.0585 0.6933 0.5657 -0.0011 0.0000 -0.0070 0.1330 0.262 + 57 -16.6722 1.4928 0.4131 0.7806 0.0669 1.7727 0.5270 -0.0232 0.0000 -0.0087 0.0681 0.266 + 58 -16.9098 1.1466 0.2292 0.5750 0.0780 1.7067 0.5074 -0.0448 0.0000 0.0138 0.0552 0.223 + 59 -17.0696 0.9138 0.1104 0.3534 0.0863 1.3246 0.3937 -0.0619 0.0000 0.0339 0.0319 0.164 + 60 -17.1499 0.7967 0.0322 0.1194 0.0909 0.5194 0.1544 -0.0454 0.0000 0.0214 0.0086 0.112 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02686 Clsurf = -0.00288 - CYsurf = -0.00434 Cmsurf = -0.13142 - CDsurf = 0.00166 Cnsurf = 0.00248 - CDisurf = 0.00166 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02668 Clsurf = -0.00287 + CYsurf = -0.00431 Cmsurf = -0.13057 + CDsurf = 0.00165 Cnsurf = 0.00246 + CDisurf = 0.00165 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16373 CDsurf = 0.01000 + CLsurf = 0.16264 CDsurf = 0.00995 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.5784 0.0963 0.1721 0.1319 0.0467 0.0000 -0.0096 -0.0372 0.322 - 62 0.0418 4.2566 0.2392 0.5245 0.0965 0.1601 0.1226 0.0124 0.0000 -0.0092 -0.0343 0.325 - 63 0.1156 4.2274 0.3930 0.5207 0.0965 0.1602 0.1227 0.0101 0.0000 -0.0088 -0.0340 0.322 - 64 0.2254 4.1839 0.5386 0.5196 0.0960 0.1616 0.1238 0.0097 0.0000 -0.0082 -0.0337 0.316 - 65 0.3698 4.1268 0.6730 0.5194 0.0950 0.1638 0.1255 0.0096 0.0000 -0.0074 -0.0334 0.309 - 66 0.5474 4.0565 0.7936 0.5190 0.0934 0.1666 0.1276 0.0095 0.0000 -0.0066 -0.0332 0.301 - 67 0.7617 3.9717 0.9441 0.5185 0.0910 0.1700 0.1302 0.0095 0.0000 -0.0057 -0.0330 0.294 - 68 1.0116 3.8728 1.0344 0.5178 0.0877 0.1741 0.1334 0.0095 0.0000 -0.0049 -0.0330 0.287 - 69 1.2891 3.7630 1.1046 0.5166 0.0837 0.1788 0.1370 0.0096 0.0000 -0.0042 -0.0332 0.280 - 70 1.5912 3.6435 1.1542 0.5154 0.0793 0.1843 0.1411 0.0097 0.0000 -0.0035 -0.0335 0.275 - 71 1.9146 3.5155 1.1831 0.5143 0.0748 0.1906 0.1460 0.0099 0.0000 -0.0030 -0.0341 0.271 - 72 2.2558 3.3805 1.1921 0.5131 0.0708 0.1978 0.1515 0.0100 0.0000 -0.0025 -0.0349 0.267 - 73 2.6109 3.2400 1.1821 0.5123 0.0676 0.2060 0.1578 0.0102 0.0000 -0.0021 -0.0359 0.263 - 74 2.9762 3.0955 1.1548 0.5113 0.0651 0.2153 0.1649 0.0104 0.0000 -0.0016 -0.0371 0.260 - 75 3.3476 2.9485 1.1122 0.5098 0.0632 0.2254 0.1726 0.0106 0.0000 -0.0011 -0.0383 0.256 - 76 3.7210 2.8008 1.0564 0.5075 0.0619 0.2362 0.1810 0.0108 0.0000 -0.0006 -0.0396 0.253 - 77 4.0924 2.6538 0.9900 0.5036 0.0611 0.2474 0.1895 0.0109 0.0000 0.0001 -0.0410 0.250 - 78 4.4577 2.5093 0.9155 0.4975 0.0607 0.2585 0.1980 0.0110 0.0000 0.0009 -0.0421 0.246 - 79 4.8128 2.3687 0.8353 0.4882 0.0608 0.2688 0.2059 0.0110 0.0000 0.0018 -0.0430 0.241 - 80 5.1540 2.2338 0.7518 0.4751 0.0614 0.2775 0.2125 0.0109 0.0000 0.0030 -0.0435 0.236 - 81 5.4774 2.1058 0.6671 0.4579 0.0623 0.2837 0.2173 0.0106 0.0000 0.0044 -0.0433 0.230 - 82 5.7795 1.9862 0.5830 0.4355 0.0636 0.2861 0.2192 0.0101 0.0000 0.0062 -0.0422 0.222 - 83 6.0570 1.8764 0.5012 0.4079 0.0651 0.2838 0.2174 0.0095 0.0000 0.0083 -0.0401 0.212 - 84 6.3069 1.7776 0.4225 0.3748 0.0667 0.2753 0.2109 0.0086 0.0000 0.0105 -0.0368 0.200 - 85 6.5264 1.6907 0.3478 0.3362 0.0683 0.2597 0.1989 0.0075 0.0000 0.0128 -0.0323 0.186 - 86 6.7314 1.6096 0.3326 0.2900 0.0698 0.2354 0.1803 0.0062 0.0000 0.0146 -0.0267 0.169 - 87 6.9144 1.5372 0.2507 0.2338 0.0712 0.1988 0.1523 0.0045 0.0000 0.0154 -0.0200 0.149 - 88 7.0535 1.4822 0.1746 0.1714 0.0723 0.1512 0.1158 0.0026 0.0000 0.0141 -0.0132 0.128 - 89 7.1471 1.4451 0.1029 0.1047 0.0730 0.0948 0.0726 0.0009 0.0000 0.0101 -0.0072 0.111 - 90 7.1941 1.4265 0.0340 0.0352 0.0734 0.0324 0.0248 -0.0007 0.0000 0.0037 -0.0023 0.102 + 61 0.0047 4.2713 0.0803 0.5721 0.0964 0.1703 0.1305 0.0459 0.0000 -0.0095 -0.0368 0.323 + 62 0.0418 4.2566 0.2392 0.5194 0.0966 0.1585 0.1214 0.0123 0.0000 -0.0091 -0.0340 0.325 + 63 0.1156 4.2274 0.3930 0.5154 0.0966 0.1586 0.1215 0.0100 0.0000 -0.0088 -0.0337 0.322 + 64 0.2254 4.1839 0.5386 0.5144 0.0961 0.1600 0.1226 0.0095 0.0000 -0.0082 -0.0334 0.317 + 65 0.3698 4.1268 0.6730 0.5143 0.0951 0.1622 0.1243 0.0095 0.0000 -0.0074 -0.0331 0.310 + 66 0.5474 4.0565 0.7936 0.5140 0.0935 0.1650 0.1264 0.0095 0.0000 -0.0065 -0.0329 0.302 + 67 0.7617 3.9717 0.9441 0.5136 0.0911 0.1684 0.1290 0.0094 0.0000 -0.0057 -0.0327 0.294 + 68 1.0116 3.8728 1.0344 0.5126 0.0879 0.1724 0.1320 0.0094 0.0000 -0.0049 -0.0327 0.287 + 69 1.2891 3.7630 1.1046 0.5116 0.0839 0.1771 0.1356 0.0095 0.0000 -0.0042 -0.0329 0.281 + 70 1.5912 3.6435 1.1542 0.5106 0.0794 0.1826 0.1398 0.0096 0.0000 -0.0035 -0.0333 0.275 + 71 1.9146 3.5155 1.1831 0.5096 0.0750 0.1888 0.1446 0.0098 0.0000 -0.0030 -0.0339 0.271 + 72 2.2558 3.3805 1.1921 0.5086 0.0710 0.1960 0.1502 0.0099 0.0000 -0.0025 -0.0347 0.267 + 73 2.6109 3.2400 1.1821 0.5081 0.0677 0.2043 0.1565 0.0102 0.0000 -0.0021 -0.0356 0.263 + 74 2.9762 3.0955 1.1548 0.5075 0.0652 0.2136 0.1636 0.0104 0.0000 -0.0016 -0.0368 0.260 + 75 3.3476 2.9485 1.1122 0.5063 0.0633 0.2238 0.1715 0.0106 0.0000 -0.0011 -0.0381 0.257 + 76 3.7210 2.8008 1.0564 0.5043 0.0620 0.2347 0.1798 0.0108 0.0000 -0.0006 -0.0394 0.253 + 77 4.0924 2.6538 0.9900 0.5008 0.0612 0.2461 0.1885 0.0109 0.0000 0.0001 -0.0407 0.250 + 78 4.4577 2.5093 0.9155 0.4949 0.0608 0.2572 0.1970 0.0110 0.0000 0.0008 -0.0419 0.246 + 79 4.8128 2.3687 0.8353 0.4860 0.0609 0.2676 0.2050 0.0110 0.0000 0.0018 -0.0429 0.241 + 80 5.1540 2.2338 0.7518 0.4734 0.0614 0.2765 0.2118 0.0109 0.0000 0.0030 -0.0433 0.236 + 81 5.4774 2.1058 0.6671 0.4563 0.0623 0.2827 0.2166 0.0106 0.0000 0.0044 -0.0432 0.230 + 82 5.7795 1.9862 0.5830 0.4342 0.0636 0.2853 0.2185 0.0101 0.0000 0.0062 -0.0421 0.222 + 83 6.0570 1.8764 0.5012 0.4069 0.0651 0.2831 0.2168 0.0095 0.0000 0.0082 -0.0400 0.212 + 84 6.3069 1.7776 0.4225 0.3740 0.0667 0.2747 0.2104 0.0086 0.0000 0.0105 -0.0367 0.200 + 85 6.5264 1.6907 0.3478 0.3355 0.0683 0.2592 0.1985 0.0075 0.0000 0.0127 -0.0322 0.186 + 86 6.7314 1.6096 0.3326 0.2895 0.0698 0.2350 0.1800 0.0062 0.0000 0.0146 -0.0266 0.169 + 87 6.9144 1.5372 0.2507 0.2334 0.0712 0.1984 0.1520 0.0045 0.0000 0.0154 -0.0199 0.149 + 88 7.0535 1.4822 0.1746 0.1712 0.0723 0.1510 0.1157 0.0027 0.0000 0.0141 -0.0132 0.128 + 89 7.1471 1.4451 0.1029 0.1045 0.0731 0.0947 0.0725 0.0010 0.0000 0.0101 -0.0072 0.111 + 90 7.1941 1.4265 0.0340 0.0352 0.0735 0.0324 0.0248 -0.0007 0.0000 0.0037 -0.0023 0.102 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02686 Clsurf = 0.00288 - CYsurf = 0.00434 Cmsurf = -0.13142 - CDsurf = 0.00166 Cnsurf = -0.00248 - CDisurf = 0.00166 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02668 Clsurf = 0.00287 + CYsurf = 0.00431 Cmsurf = -0.13057 + CDsurf = 0.00165 Cnsurf = -0.00246 + CDisurf = 0.00165 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.16373 CDsurf = 0.01000 + CLsurf = 0.16264 CDsurf = 0.00995 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.5784 0.0963 0.1721 0.1319 0.0468 0.0000 -0.0096 0.0372 0.322 - 92 -0.0418 4.2566 0.2392 0.5245 0.0965 0.1601 0.1226 0.0124 0.0000 -0.0092 0.0343 0.325 - 93 -0.1156 4.2274 0.3930 0.5207 0.0965 0.1602 0.1227 0.0101 0.0000 -0.0088 0.0340 0.322 - 94 -0.2254 4.1839 0.5386 0.5196 0.0960 0.1616 0.1238 0.0097 0.0000 -0.0082 0.0337 0.316 - 95 -0.3698 4.1268 0.6730 0.5194 0.0950 0.1638 0.1255 0.0096 0.0000 -0.0074 0.0334 0.309 - 96 -0.5474 4.0565 0.7936 0.5190 0.0934 0.1666 0.1276 0.0095 0.0000 -0.0066 0.0332 0.301 - 97 -0.7617 3.9717 0.9441 0.5185 0.0910 0.1700 0.1302 0.0095 0.0000 -0.0057 0.0330 0.294 - 98 -1.0116 3.8728 1.0344 0.5178 0.0877 0.1741 0.1334 0.0095 0.0000 -0.0049 0.0330 0.287 - 99 -1.2891 3.7630 1.1046 0.5166 0.0837 0.1788 0.1370 0.0096 0.0000 -0.0042 0.0332 0.280 - 100 -1.5912 3.6435 1.1542 0.5154 0.0793 0.1843 0.1411 0.0097 0.0000 -0.0035 0.0335 0.275 - 101 -1.9146 3.5155 1.1831 0.5143 0.0748 0.1906 0.1460 0.0099 0.0000 -0.0030 0.0341 0.271 - 102 -2.2558 3.3805 1.1921 0.5131 0.0708 0.1978 0.1515 0.0100 0.0000 -0.0025 0.0349 0.267 - 103 -2.6109 3.2400 1.1821 0.5123 0.0676 0.2060 0.1578 0.0102 0.0000 -0.0021 0.0359 0.263 - 104 -2.9762 3.0955 1.1548 0.5113 0.0651 0.2153 0.1649 0.0104 0.0000 -0.0016 0.0370 0.260 - 105 -3.3476 2.9485 1.1122 0.5098 0.0632 0.2254 0.1726 0.0106 0.0000 -0.0011 0.0383 0.256 - 106 -3.7210 2.8008 1.0564 0.5075 0.0619 0.2362 0.1809 0.0108 0.0000 -0.0006 0.0396 0.253 - 107 -4.0924 2.6538 0.9900 0.5036 0.0611 0.2474 0.1895 0.0109 0.0000 0.0001 0.0410 0.250 - 108 -4.4577 2.5093 0.9155 0.4975 0.0607 0.2585 0.1980 0.0110 0.0000 0.0009 0.0421 0.246 - 109 -4.8128 2.3687 0.8353 0.4881 0.0608 0.2688 0.2059 0.0110 0.0000 0.0018 0.0430 0.241 - 110 -5.1540 2.2338 0.7518 0.4751 0.0614 0.2775 0.2125 0.0109 0.0000 0.0030 0.0435 0.236 - 111 -5.4774 2.1058 0.6671 0.4578 0.0623 0.2837 0.2173 0.0106 0.0000 0.0044 0.0433 0.230 - 112 -5.7795 1.9862 0.5830 0.4354 0.0636 0.2861 0.2192 0.0101 0.0000 0.0062 0.0422 0.222 - 113 -6.0570 1.8764 0.5012 0.4079 0.0651 0.2838 0.2174 0.0095 0.0000 0.0083 0.0401 0.212 - 114 -6.3069 1.7776 0.4225 0.3748 0.0667 0.2753 0.2109 0.0086 0.0000 0.0105 0.0368 0.200 - 115 -6.5264 1.6907 0.3478 0.3362 0.0682 0.2597 0.1989 0.0075 0.0000 0.0128 0.0323 0.186 - 116 -6.7314 1.6096 0.3326 0.2900 0.0698 0.2354 0.1803 0.0062 0.0000 0.0146 0.0267 0.169 - 117 -6.9144 1.5372 0.2507 0.2338 0.0712 0.1988 0.1523 0.0045 0.0000 0.0154 0.0200 0.149 - 118 -7.0535 1.4822 0.1746 0.1714 0.0723 0.1512 0.1158 0.0026 0.0000 0.0141 0.0132 0.128 - 119 -7.1471 1.4451 0.1029 0.1047 0.0730 0.0948 0.0726 0.0009 0.0000 0.0101 0.0072 0.111 - 120 -7.1941 1.4265 0.0340 0.0352 0.0734 0.0324 0.0248 -0.0007 0.0000 0.0037 0.0023 0.102 + 91 -0.0047 4.2713 0.0803 0.5721 0.0964 0.1703 0.1305 0.0459 0.0000 -0.0095 0.0368 0.323 + 92 -0.0418 4.2566 0.2392 0.5194 0.0966 0.1585 0.1214 0.0123 0.0000 -0.0091 0.0340 0.325 + 93 -0.1156 4.2274 0.3930 0.5154 0.0966 0.1586 0.1215 0.0100 0.0000 -0.0088 0.0337 0.322 + 94 -0.2254 4.1839 0.5386 0.5144 0.0961 0.1600 0.1226 0.0095 0.0000 -0.0082 0.0334 0.317 + 95 -0.3698 4.1268 0.6730 0.5143 0.0951 0.1622 0.1243 0.0095 0.0000 -0.0074 0.0331 0.310 + 96 -0.5474 4.0565 0.7936 0.5140 0.0935 0.1650 0.1264 0.0095 0.0000 -0.0065 0.0329 0.302 + 97 -0.7617 3.9717 0.9441 0.5136 0.0911 0.1684 0.1290 0.0094 0.0000 -0.0057 0.0327 0.294 + 98 -1.0116 3.8728 1.0344 0.5126 0.0879 0.1724 0.1320 0.0094 0.0000 -0.0049 0.0327 0.287 + 99 -1.2891 3.7630 1.1046 0.5116 0.0839 0.1771 0.1356 0.0095 0.0000 -0.0042 0.0329 0.281 + 100 -1.5912 3.6435 1.1542 0.5106 0.0794 0.1826 0.1398 0.0096 0.0000 -0.0035 0.0333 0.275 + 101 -1.9146 3.5155 1.1831 0.5096 0.0750 0.1888 0.1446 0.0098 0.0000 -0.0030 0.0339 0.271 + 102 -2.2558 3.3805 1.1921 0.5086 0.0710 0.1960 0.1502 0.0099 0.0000 -0.0025 0.0347 0.267 + 103 -2.6109 3.2400 1.1821 0.5081 0.0677 0.2043 0.1565 0.0102 0.0000 -0.0021 0.0356 0.263 + 104 -2.9762 3.0955 1.1548 0.5075 0.0652 0.2136 0.1636 0.0104 0.0000 -0.0016 0.0368 0.260 + 105 -3.3476 2.9485 1.1122 0.5063 0.0633 0.2238 0.1715 0.0106 0.0000 -0.0011 0.0381 0.257 + 106 -3.7210 2.8008 1.0564 0.5043 0.0620 0.2347 0.1798 0.0108 0.0000 -0.0006 0.0394 0.253 + 107 -4.0924 2.6538 0.9900 0.5008 0.0612 0.2461 0.1885 0.0109 0.0000 0.0001 0.0407 0.250 + 108 -4.4577 2.5093 0.9155 0.4949 0.0608 0.2572 0.1970 0.0110 0.0000 0.0008 0.0419 0.246 + 109 -4.8128 2.3687 0.8353 0.4860 0.0609 0.2676 0.2050 0.0110 0.0000 0.0018 0.0429 0.241 + 110 -5.1540 2.2338 0.7518 0.4734 0.0614 0.2765 0.2118 0.0109 0.0000 0.0030 0.0433 0.236 + 111 -5.4774 2.1058 0.6671 0.4563 0.0623 0.2827 0.2166 0.0106 0.0000 0.0044 0.0432 0.230 + 112 -5.7795 1.9862 0.5830 0.4342 0.0636 0.2853 0.2185 0.0101 0.0000 0.0062 0.0421 0.222 + 113 -6.0570 1.8764 0.5012 0.4069 0.0651 0.2831 0.2168 0.0095 0.0000 0.0082 0.0400 0.212 + 114 -6.3069 1.7776 0.4225 0.3740 0.0667 0.2747 0.2104 0.0086 0.0000 0.0105 0.0367 0.200 + 115 -6.5264 1.6907 0.3478 0.3355 0.0683 0.2592 0.1985 0.0075 0.0000 0.0127 0.0322 0.186 + 116 -6.7314 1.6096 0.3326 0.2895 0.0698 0.2350 0.1800 0.0062 0.0000 0.0146 0.0266 0.169 + 117 -6.9144 1.5372 0.2507 0.2334 0.0712 0.1984 0.1520 0.0045 0.0000 0.0154 0.0199 0.149 + 118 -7.0535 1.4822 0.1746 0.1712 0.0723 0.1510 0.1157 0.0027 0.0000 0.0141 0.0132 0.128 + 119 -7.1471 1.4451 0.1029 0.1045 0.0731 0.0946 0.0725 0.0010 0.0000 0.0101 0.0072 0.111 + 120 -7.1941 1.4265 0.0340 0.0352 0.0735 0.0324 0.0248 -0.0007 0.0000 0.0037 0.0023 0.102 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,68 +198,68 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.402 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.411 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.421 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.431 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.433 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.431 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.427 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.413 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.386 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.342 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.303 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.288 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.281 + 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.423 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.430 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.431 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.443 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.443 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.440 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.431 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.407 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.382 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.341 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.299 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.287 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.282 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.273 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.263 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.251 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.242 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.265 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.260 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.253 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.248 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.233 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.228 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.217 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.203 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.191 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.173 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.151 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.129 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.112 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.102 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.207 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.189 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.175 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.153 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.132 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.101 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00608 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.04461 + CLsurf = 0.00600 Clsurf = 0.00000 + CYsurf = 0.00000 Cmsurf = 0.04468 CDsurf = -0.00018 Cnsurf = -0.00000 CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00613 CDsurf = -0.00018 + CLsurf = 0.00605 CDsurf = -0.00019 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.1323 0.1313 0.0600 0.0052 -0.0021 0.0000 0.0034 0.0003 -0.409 - 152 -1.3090 31.2096 11.6724 0.1947 0.1436 0.0241 0.0063 -0.0007 0.0000 0.0042 0.0006 -0.408 - 153 -0.9350 34.0626 12.7394 0.2156 0.1362 0.0154 0.0064 -0.0001 0.0000 0.0049 0.0011 -0.521 - 154 -0.5610 36.1619 13.5246 0.2287 0.1354 0.0106 0.0063 0.0003 0.0000 0.0052 0.0016 -0.579 - 155 -0.1870 37.5332 14.0374 0.2366 0.1370 0.0072 0.0062 0.0010 0.0000 0.0053 0.0026 -0.602 - 156 0.1870 37.5332 14.0374 0.2366 0.1370 0.0072 0.0062 0.0010 0.0000 0.0053 0.0026 -0.602 - 157 0.5610 36.1619 13.5246 0.2287 0.1354 0.0106 0.0063 0.0003 0.0000 0.0052 0.0016 -0.579 - 158 0.9350 34.0626 12.7394 0.2156 0.1362 0.0154 0.0064 -0.0001 0.0000 0.0049 0.0011 -0.521 - 159 1.3090 31.2096 11.6724 0.1947 0.1436 0.0241 0.0063 -0.0007 0.0000 0.0042 0.0006 -0.408 - 160 1.6830 26.5957 9.9468 0.1323 0.1313 0.0600 0.0052 -0.0021 0.0000 0.0034 0.0003 -0.409 + 151 -1.6830 26.5957 9.9468 0.1304 0.1313 0.0591 0.0051 -0.0021 0.0000 0.0034 0.0003 -0.423 + 152 -1.3090 31.2096 11.6724 0.1921 0.1436 0.0238 0.0062 -0.0007 0.0000 0.0042 0.0007 -0.420 + 153 -0.9350 34.0626 12.7394 0.2130 0.1364 0.0152 0.0063 -0.0001 0.0000 0.0049 0.0011 -0.534 + 154 -0.5610 36.1619 13.5246 0.2262 0.1356 0.0104 0.0062 0.0003 0.0000 0.0053 0.0017 -0.591 + 155 -0.1870 37.5332 14.0374 0.2341 0.1372 0.0072 0.0062 0.0010 0.0000 0.0053 0.0026 -0.614 + 156 0.1870 37.5332 14.0374 0.2341 0.1372 0.0072 0.0062 0.0010 0.0000 0.0053 0.0026 -0.614 + 157 0.5610 36.1619 13.5246 0.2262 0.1356 0.0104 0.0062 0.0003 0.0000 0.0053 0.0017 -0.591 + 158 0.9350 34.0626 12.7394 0.2130 0.1364 0.0152 0.0063 -0.0001 0.0000 0.0049 0.0011 -0.534 + 159 1.3090 31.2096 11.6724 0.1921 0.1436 0.0238 0.0062 -0.0007 0.0000 0.0042 0.0007 -0.420 + 160 1.6830 26.5957 9.9468 0.1304 0.1313 0.0591 0.0051 -0.0021 0.0000 0.0034 0.0003 -0.423 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00000 Clsurf = -0.00000 + CLsurf = -0.00000 Clsurf = -0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 + CDsurf = 0.00000 Cnsurf = 0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 -0.316 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.391 - 163 0.0000 34.0626 12.7394 -0.0000 0.0001 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.247 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.117 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.042 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.323 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.438 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.532 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.608 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.691 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.774 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.518 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.258 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.017 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.283 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.412 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.509 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.588 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.673 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_05_05.txt b/regression/scripts/AVL/avl_files/strip_forces_case_05_05.txt index 0d6a528e95..89c3593763 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_05_05.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_05_05.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.44422 Clsurf = -0.08783 - CYsurf = -0.02533 Cmsurf = -0.40756 - CDsurf = 0.01702 Cnsurf = -0.00839 - CDisurf = 0.01702 CDvsurf = 0.00000 + CLsurf = 0.44518 Clsurf = -0.08793 + CYsurf = -0.02521 Cmsurf = -0.40805 + CDsurf = 0.01683 Cnsurf = -0.00840 + CDisurf = 0.01683 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.86842 CDsurf = 0.03323 + CLsurf = 0.87027 CDsurf = 0.03285 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 5.6898 0.1813 0.8178 0.6334 0.8620 0.0000 -0.0470 -0.1892 0.324 - 2 0.1025 7.6885 1.0492 5.0830 0.1810 0.8353 0.6470 0.1553 0.0000 -0.0459 -0.1734 0.321 - 3 0.2837 7.5620 1.7073 5.0320 0.1797 0.8481 0.6569 0.1102 0.0000 -0.0435 -0.1724 0.316 - 4 0.5530 7.3741 2.3052 5.0064 0.1768 0.8676 0.6720 0.0979 0.0000 -0.0396 -0.1720 0.309 - 5 0.9075 7.1267 2.8223 4.9698 0.1710 0.8928 0.6915 0.0903 0.0000 -0.0351 -0.1722 0.301 - 6 1.3432 6.8226 3.2414 4.9151 0.1586 0.9242 0.7158 0.0814 0.0000 -0.0308 -0.1734 0.293 - 7 1.8554 6.4651 3.5491 4.8292 0.1335 0.9600 0.7436 0.0732 0.0000 -0.0272 -0.1759 0.287 - 8 2.4386 6.0582 3.7368 4.7075 0.1085 1.0014 0.7756 0.0590 0.0000 -0.0247 -0.1802 0.282 - 9 3.0862 5.6062 3.8005 4.5423 0.0951 1.0467 0.8107 0.0453 0.0000 -0.0238 -0.1862 0.279 - 10 3.7613 5.1351 3.4440 4.3455 0.0834 1.0949 0.8480 0.0375 0.0000 -0.0243 -0.1941 0.279 - 11 4.4532 4.6522 3.3149 4.1448 0.0695 1.1554 0.8949 0.0225 0.0000 -0.0262 -0.2049 0.279 - 12 5.1831 4.1429 3.0930 3.9193 0.0477 1.2297 0.9524 0.0060 0.0000 -0.0281 -0.2177 0.279 - 13 6.0123 3.7903 3.4706 3.6671 0.0326 1.1966 0.9749 -0.0011 0.0000 -0.0241 -0.2402 0.275 - 14 6.9353 3.6075 3.3775 3.4764 0.0310 1.1916 0.9708 0.0008 0.0000 -0.0237 -0.2389 0.274 - 15 7.8737 3.4215 3.2389 3.3016 0.0273 1.1932 0.9721 0.0003 0.0000 -0.0232 -0.2388 0.274 - 16 8.8172 3.2345 3.0619 3.1336 0.0250 1.1981 0.9762 -0.0008 0.0000 -0.0227 -0.2392 0.273 - 17 9.7556 3.0486 2.8543 2.9676 0.0247 1.2040 0.9810 -0.0021 0.0000 -0.0222 -0.2398 0.273 - 18 10.6786 2.8657 2.6240 2.8028 0.0258 1.2100 0.9858 -0.0035 0.0000 -0.0216 -0.2403 0.272 - 19 11.5760 2.6879 2.3787 2.6383 0.0279 1.2145 0.9895 -0.0048 0.0000 -0.0208 -0.2404 0.271 - 20 12.4328 2.5181 2.1010 2.4738 0.0310 1.2158 0.9905 -0.0062 0.0000 -0.0197 -0.2396 0.270 - 21 13.2400 2.3582 1.8520 2.3078 0.0353 1.2113 0.9869 -0.0074 0.0000 -0.0180 -0.2373 0.268 - 22 13.9941 2.2087 1.6074 2.1368 0.0412 1.1976 0.9757 -0.0084 0.0000 -0.0153 -0.2324 0.266 - 23 14.6868 2.0715 1.3716 1.9560 0.0489 1.1690 0.9525 -0.0092 0.0000 -0.0113 -0.2236 0.262 - 24 15.3105 1.9479 1.1479 1.7589 0.0581 1.1180 0.9109 -0.0096 0.0000 -0.0060 -0.2096 0.257 - 25 15.8583 1.8393 0.9381 1.5375 0.0678 1.0349 0.8432 -0.0083 0.0000 -0.0013 -0.1903 0.252 - 26 16.3244 1.7470 0.7427 1.2875 0.0780 0.9115 0.7426 -0.0008 0.0000 -0.0041 -0.1704 0.256 - 27 16.6722 1.4928 0.4131 1.0202 0.0886 2.3170 0.6936 -0.0398 0.0000 -0.0072 -0.0886 0.260 - 28 16.9098 1.1466 0.2292 0.7506 0.1021 2.2358 0.6692 -0.0773 0.0000 0.0221 -0.0717 0.217 - 29 17.0696 0.9138 0.1104 0.4608 0.1119 1.7422 0.5215 -0.1071 0.0000 0.0477 -0.0412 0.159 - 30 17.1499 0.7967 0.0322 0.1554 0.1167 0.6901 0.2066 -0.0797 0.0000 0.0295 -0.0109 0.107 + 1 0.0114 7.7520 0.3539 5.7117 0.1812 0.8212 0.6360 0.8640 0.0000 -0.0488 -0.1912 0.327 + 2 0.1025 7.6885 1.0491 5.1004 0.1809 0.8383 0.6493 0.1553 0.0000 -0.0473 -0.1751 0.323 + 3 0.2837 7.5620 1.7073 5.0492 0.1799 0.8511 0.6592 0.1101 0.0000 -0.0449 -0.1741 0.318 + 4 0.5530 7.3741 2.3052 5.0233 0.1772 0.8707 0.6744 0.0973 0.0000 -0.0411 -0.1737 0.311 + 5 0.9075 7.1267 2.8223 4.9873 0.1716 0.8962 0.6942 0.0886 0.0000 -0.0366 -0.1739 0.303 + 6 1.3432 6.8226 3.2414 4.9308 0.1592 0.9273 0.7182 0.0809 0.0000 -0.0322 -0.1751 0.295 + 7 1.8554 6.4651 3.5491 4.8401 0.1342 0.9635 0.7463 0.0648 0.0000 -0.0287 -0.1776 0.288 + 8 2.4386 6.0582 3.7368 4.7169 0.1093 1.0038 0.7775 0.0566 0.0000 -0.0261 -0.1816 0.284 + 9 3.0862 5.6062 3.8005 4.5553 0.0963 1.0495 0.8129 0.0470 0.0000 -0.0250 -0.1877 0.281 + 10 3.7613 5.1351 3.4440 4.3661 0.0843 1.0998 0.8518 0.0394 0.0000 -0.0251 -0.1956 0.280 + 11 4.4532 4.6522 3.3149 4.1893 0.0694 1.1672 0.9039 0.0269 0.0000 -0.0248 -0.2056 0.277 + 12 5.1831 4.1429 3.0930 3.9307 0.0468 1.2335 0.9553 0.0050 0.0000 -0.0263 -0.2168 0.278 + 13 6.0123 3.7903 3.4706 3.6702 0.0320 1.1976 0.9757 -0.0010 0.0000 -0.0224 -0.2389 0.273 + 14 6.9353 3.6075 3.3775 3.4784 0.0307 1.1923 0.9714 0.0008 0.0000 -0.0219 -0.2375 0.273 + 15 7.8737 3.4215 3.2389 3.3033 0.0272 1.1938 0.9726 0.0003 0.0000 -0.0213 -0.2372 0.272 + 16 8.8172 3.2345 3.0619 3.1355 0.0249 1.1988 0.9767 -0.0008 0.0000 -0.0207 -0.2376 0.271 + 17 9.7556 3.0486 2.8543 2.9692 0.0246 1.2047 0.9815 -0.0023 0.0000 -0.0202 -0.2382 0.271 + 18 10.6786 2.8657 2.6239 2.8042 0.0257 1.2106 0.9863 -0.0036 0.0000 -0.0196 -0.2387 0.270 + 19 11.5760 2.6879 2.3787 2.6394 0.0279 1.2150 0.9899 -0.0049 0.0000 -0.0188 -0.2388 0.269 + 20 12.4328 2.5181 2.1010 2.4747 0.0310 1.2162 0.9909 -0.0063 0.0000 -0.0177 -0.2380 0.268 + 21 13.2400 2.3582 1.8520 2.3086 0.0353 1.2117 0.9872 -0.0075 0.0000 -0.0160 -0.2356 0.266 + 22 13.9941 2.2087 1.6074 2.1375 0.0412 1.1980 0.9760 -0.0086 0.0000 -0.0133 -0.2307 0.264 + 23 14.6868 2.0715 1.3716 1.9563 0.0489 1.1692 0.9526 -0.0093 0.0000 -0.0093 -0.2219 0.260 + 24 15.3105 1.9479 1.1479 1.7590 0.0580 1.1181 0.9110 -0.0097 0.0000 -0.0040 -0.2078 0.254 + 25 15.8583 1.8393 0.9381 1.5374 0.0677 1.0349 0.8432 -0.0085 0.0000 0.0007 -0.1885 0.249 + 26 16.3244 1.7470 0.7427 1.2868 0.0775 0.9110 0.7423 -0.0009 0.0000 -0.0022 -0.1686 0.253 + 27 16.6722 1.4928 0.4131 1.0196 0.0882 2.3159 0.6932 -0.0402 0.0000 -0.0056 -0.0879 0.258 + 28 16.9098 1.1466 0.2292 0.7503 0.1020 2.2350 0.6690 -0.0776 0.0000 0.0234 -0.0711 0.215 + 29 17.0696 0.9138 0.1104 0.4607 0.1120 1.7420 0.5214 -0.1075 0.0000 0.0485 -0.0408 0.157 + 30 17.1499 0.7967 0.0322 0.1555 0.1174 0.6905 0.2067 -0.0803 0.0000 0.0298 -0.0108 0.106 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.44421 Clsurf = 0.08783 - CYsurf = 0.02533 Cmsurf = -0.40756 - CDsurf = 0.01702 Cnsurf = 0.00839 - CDisurf = 0.01702 CDvsurf = 0.00000 + CLsurf = 0.44518 Clsurf = 0.08793 + CYsurf = 0.02521 Cmsurf = -0.40804 + CDsurf = 0.01683 Cnsurf = 0.00840 + CDisurf = 0.01683 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.86841 CDsurf = 0.03323 + CLsurf = 0.87027 CDsurf = 0.03285 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 5.6898 0.1815 0.8178 0.6334 0.8621 0.0000 -0.0470 0.1892 0.324 - 32 -0.1025 7.6885 1.0492 5.0830 0.1810 0.8353 0.6470 0.1553 0.0000 -0.0459 0.1734 0.321 - 33 -0.2837 7.5620 1.7073 5.0320 0.1797 0.8481 0.6569 0.1102 0.0000 -0.0435 0.1724 0.316 - 34 -0.5530 7.3741 2.3052 5.0064 0.1768 0.8676 0.6720 0.0979 0.0000 -0.0396 0.1720 0.309 - 35 -0.9075 7.1267 2.8223 4.9698 0.1710 0.8928 0.6915 0.0903 0.0000 -0.0351 0.1722 0.301 - 36 -1.3432 6.8226 3.2414 4.9151 0.1586 0.9242 0.7158 0.0814 0.0000 -0.0308 0.1734 0.293 - 37 -1.8554 6.4651 3.5491 4.8292 0.1335 0.9600 0.7436 0.0732 0.0000 -0.0272 0.1759 0.287 - 38 -2.4386 6.0582 3.7368 4.7075 0.1085 1.0014 0.7756 0.0590 0.0000 -0.0247 0.1802 0.282 - 39 -3.0862 5.6062 3.8005 4.5423 0.0951 1.0467 0.8107 0.0453 0.0000 -0.0238 0.1862 0.279 - 40 -3.7613 5.1351 3.4440 4.3455 0.0834 1.0949 0.8480 0.0375 0.0000 -0.0243 0.1941 0.279 - 41 -4.4532 4.6522 3.3149 4.1448 0.0695 1.1554 0.8949 0.0225 0.0000 -0.0262 0.2049 0.279 - 42 -5.1831 4.1429 3.0930 3.9193 0.0477 1.2297 0.9524 0.0060 0.0000 -0.0281 0.2177 0.279 - 43 -6.0123 3.7903 3.4706 3.6671 0.0326 1.1965 0.9749 -0.0011 0.0000 -0.0241 0.2402 0.275 - 44 -6.9353 3.6075 3.3775 3.4764 0.0310 1.1915 0.9708 0.0008 0.0000 -0.0237 0.2389 0.274 - 45 -7.8737 3.4215 3.2389 3.3015 0.0273 1.1932 0.9721 0.0003 0.0000 -0.0232 0.2388 0.274 - 46 -8.8172 3.2345 3.0619 3.1335 0.0250 1.1981 0.9761 -0.0008 0.0000 -0.0227 0.2392 0.273 - 47 -9.7556 3.0486 2.8543 2.9675 0.0247 1.2040 0.9810 -0.0021 0.0000 -0.0222 0.2398 0.273 - 48 -10.6786 2.8657 2.6240 2.8027 0.0258 1.2099 0.9858 -0.0035 0.0000 -0.0216 0.2403 0.272 - 49 -11.5760 2.6879 2.3787 2.6382 0.0279 1.2145 0.9895 -0.0048 0.0000 -0.0208 0.2404 0.271 - 50 -12.4328 2.5181 2.1010 2.4738 0.0310 1.2157 0.9905 -0.0062 0.0000 -0.0197 0.2396 0.270 - 51 -13.2400 2.3582 1.8520 2.3078 0.0353 1.2113 0.9869 -0.0074 0.0000 -0.0180 0.2373 0.268 - 52 -13.9941 2.2087 1.6074 2.1368 0.0412 1.1976 0.9757 -0.0084 0.0000 -0.0153 0.2324 0.266 - 53 -14.6868 2.0715 1.3716 1.9559 0.0489 1.1690 0.9524 -0.0092 0.0000 -0.0113 0.2236 0.262 - 54 -15.3105 1.9479 1.1479 1.7588 0.0581 1.1180 0.9109 -0.0096 0.0000 -0.0060 0.2096 0.257 - 55 -15.8583 1.8393 0.9381 1.5375 0.0678 1.0349 0.8432 -0.0083 0.0000 -0.0013 0.1903 0.252 - 56 -16.3244 1.7470 0.7427 1.2875 0.0780 0.9115 0.7426 -0.0008 0.0000 -0.0041 0.1704 0.256 - 57 -16.6722 1.4928 0.4131 1.0202 0.0886 2.3170 0.6936 -0.0398 0.0000 -0.0072 0.0886 0.260 - 58 -16.9098 1.1466 0.2292 0.7506 0.1021 2.2357 0.6692 -0.0773 0.0000 0.0221 0.0717 0.217 - 59 -17.0696 0.9138 0.1104 0.4608 0.1119 1.7421 0.5215 -0.1071 0.0000 0.0477 0.0412 0.159 - 60 -17.1499 0.7967 0.0322 0.1554 0.1167 0.6901 0.2066 -0.0797 0.0000 0.0295 0.0109 0.107 + 31 -0.0114 7.7520 0.3539 5.7117 0.1812 0.8212 0.6360 0.8640 0.0000 -0.0488 0.1912 0.327 + 32 -0.1025 7.6885 1.0491 5.1004 0.1809 0.8383 0.6493 0.1553 0.0000 -0.0473 0.1751 0.323 + 33 -0.2837 7.5620 1.7073 5.0492 0.1799 0.8511 0.6592 0.1101 0.0000 -0.0449 0.1741 0.318 + 34 -0.5530 7.3741 2.3052 5.0233 0.1772 0.8707 0.6744 0.0973 0.0000 -0.0411 0.1737 0.311 + 35 -0.9075 7.1267 2.8223 4.9873 0.1716 0.8962 0.6942 0.0886 0.0000 -0.0366 0.1739 0.303 + 36 -1.3432 6.8226 3.2414 4.9308 0.1592 0.9273 0.7182 0.0809 0.0000 -0.0322 0.1751 0.295 + 37 -1.8554 6.4651 3.5491 4.8401 0.1342 0.9635 0.7463 0.0648 0.0000 -0.0287 0.1776 0.288 + 38 -2.4386 6.0582 3.7368 4.7169 0.1093 1.0038 0.7775 0.0566 0.0000 -0.0261 0.1816 0.284 + 39 -3.0862 5.6062 3.8005 4.5553 0.0963 1.0495 0.8129 0.0470 0.0000 -0.0250 0.1877 0.281 + 40 -3.7613 5.1351 3.4440 4.3661 0.0843 1.0998 0.8518 0.0394 0.0000 -0.0251 0.1956 0.280 + 41 -4.4532 4.6522 3.3149 4.1893 0.0694 1.1672 0.9039 0.0269 0.0000 -0.0248 0.2056 0.277 + 42 -5.1831 4.1429 3.0930 3.9306 0.0468 1.2334 0.9553 0.0050 0.0000 -0.0263 0.2168 0.278 + 43 -6.0123 3.7903 3.4706 3.6702 0.0320 1.1976 0.9757 -0.0010 0.0000 -0.0224 0.2389 0.273 + 44 -6.9353 3.6075 3.3775 3.4784 0.0307 1.1922 0.9714 0.0008 0.0000 -0.0219 0.2375 0.273 + 45 -7.8737 3.4215 3.2389 3.3033 0.0272 1.1938 0.9726 0.0003 0.0000 -0.0213 0.2372 0.272 + 46 -8.8172 3.2345 3.0619 3.1355 0.0249 1.1988 0.9767 -0.0008 0.0000 -0.0207 0.2376 0.271 + 47 -9.7556 3.0486 2.8543 2.9692 0.0246 1.2047 0.9815 -0.0023 0.0000 -0.0202 0.2382 0.271 + 48 -10.6786 2.8657 2.6239 2.8042 0.0257 1.2106 0.9863 -0.0036 0.0000 -0.0196 0.2387 0.270 + 49 -11.5760 2.6879 2.3787 2.6394 0.0279 1.2150 0.9899 -0.0049 0.0000 -0.0188 0.2388 0.269 + 50 -12.4328 2.5181 2.1010 2.4747 0.0310 1.2162 0.9909 -0.0063 0.0000 -0.0177 0.2380 0.268 + 51 -13.2400 2.3582 1.8520 2.3086 0.0353 1.2117 0.9872 -0.0075 0.0000 -0.0160 0.2356 0.266 + 52 -13.9941 2.2087 1.6074 2.1375 0.0412 1.1980 0.9760 -0.0086 0.0000 -0.0133 0.2307 0.264 + 53 -14.6868 2.0715 1.3716 1.9563 0.0489 1.1692 0.9526 -0.0093 0.0000 -0.0093 0.2219 0.260 + 54 -15.3105 1.9479 1.1479 1.7590 0.0580 1.1181 0.9110 -0.0097 0.0000 -0.0040 0.2078 0.254 + 55 -15.8583 1.8393 0.9381 1.5374 0.0677 1.0349 0.8432 -0.0085 0.0000 0.0007 0.1885 0.249 + 56 -16.3244 1.7470 0.7427 1.2868 0.0775 0.9110 0.7423 -0.0009 0.0000 -0.0022 0.1686 0.253 + 57 -16.6722 1.4928 0.4131 1.0196 0.0882 2.3159 0.6932 -0.0402 0.0000 -0.0056 0.0879 0.258 + 58 -16.9098 1.1466 0.2292 0.7503 0.1020 2.2349 0.6690 -0.0776 0.0000 0.0234 0.0711 0.215 + 59 -17.0696 0.9138 0.1104 0.4607 0.1120 1.7420 0.5214 -0.1075 0.0000 0.0485 0.0408 0.157 + 60 -17.1499 0.7967 0.0322 0.1555 0.1174 0.6905 0.2067 -0.0803 0.0000 0.0298 0.0108 0.106 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04370 Clsurf = -0.00458 - CYsurf = -0.00708 Cmsurf = -0.21395 - CDsurf = 0.00356 Cnsurf = 0.00394 - CDisurf = 0.00356 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04352 Clsurf = -0.00457 + CYsurf = -0.00706 Cmsurf = -0.21310 + CDsurf = 0.00355 Cnsurf = 0.00392 + CDisurf = 0.00355 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.26642 CDsurf = 0.02144 + CLsurf = 0.26533 CDsurf = 0.02136 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.0570 0.1298 0.3055 0.2332 0.1318 0.0000 -0.0154 -0.0665 0.316 - 62 0.0418 4.2566 0.2392 0.8996 0.1303 0.2740 0.2092 0.0305 0.0000 -0.0145 -0.0582 0.320 - 63 0.1156 4.2274 0.3930 0.8880 0.1304 0.2735 0.2087 0.0238 0.0000 -0.0139 -0.0575 0.317 - 64 0.2254 4.1839 0.5386 0.8847 0.1299 0.2755 0.2103 0.0224 0.0000 -0.0129 -0.0569 0.311 - 65 0.3698 4.1268 0.6730 0.8836 0.1287 0.2791 0.2130 0.0219 0.0000 -0.0115 -0.0563 0.304 - 66 0.5474 4.0565 0.7936 0.8820 0.1266 0.2835 0.2164 0.0217 0.0000 -0.0100 -0.0558 0.296 - 67 0.7617 3.9717 0.9441 0.8803 0.1233 0.2891 0.2207 0.0215 0.0000 -0.0085 -0.0554 0.288 - 68 1.0116 3.8728 1.0344 0.8781 0.1188 0.2958 0.2258 0.0214 0.0000 -0.0070 -0.0554 0.281 - 69 1.2891 3.7630 1.1046 0.8741 0.1131 0.3032 0.2314 0.0214 0.0000 -0.0058 -0.0555 0.275 - 70 1.5912 3.6435 1.1542 0.8696 0.1067 0.3116 0.2378 0.0214 0.0000 -0.0047 -0.0560 0.270 - 71 1.9146 3.5155 1.1831 0.8645 0.1003 0.3211 0.2451 0.0216 0.0000 -0.0037 -0.0568 0.265 - 72 2.2558 3.3805 1.1921 0.8578 0.0947 0.3315 0.2530 0.0216 0.0000 -0.0029 -0.0578 0.262 - 73 2.6109 3.2400 1.1821 0.8514 0.0902 0.3433 0.2620 0.0219 0.0000 -0.0022 -0.0592 0.258 - 74 2.9762 3.0955 1.1548 0.8434 0.0869 0.3561 0.2718 0.0222 0.0000 -0.0014 -0.0607 0.255 - 75 3.3476 2.9485 1.1122 0.8341 0.0847 0.3698 0.2823 0.0222 0.0000 -0.0007 -0.0623 0.252 - 76 3.7210 2.8008 1.0564 0.8231 0.0832 0.3843 0.2933 0.0224 0.0000 0.0001 -0.0640 0.250 - 77 4.0924 2.6538 0.9900 0.8093 0.0823 0.3989 0.3045 0.0225 0.0000 0.0011 -0.0657 0.246 - 78 4.4577 2.5093 0.9155 0.7924 0.0821 0.4132 0.3154 0.0225 0.0000 0.0022 -0.0671 0.243 - 79 4.8128 2.3687 0.8353 0.7709 0.0825 0.4260 0.3251 0.0222 0.0000 0.0036 -0.0680 0.239 - 80 5.1540 2.2338 0.7518 0.7441 0.0835 0.4362 0.3329 0.0218 0.0000 0.0053 -0.0683 0.234 - 81 5.4774 2.1058 0.6671 0.7121 0.0851 0.4430 0.3381 0.0211 0.0000 0.0074 -0.0676 0.228 - 82 5.7795 1.9862 0.5830 0.6728 0.0871 0.4439 0.3388 0.0199 0.0000 0.0100 -0.0656 0.221 - 83 6.0570 1.8764 0.5012 0.6268 0.0895 0.4380 0.3343 0.0185 0.0000 0.0130 -0.0621 0.211 - 84 6.3069 1.7776 0.4225 0.5732 0.0919 0.4230 0.3228 0.0167 0.0000 0.0163 -0.0567 0.199 - 85 6.5264 1.6907 0.3478 0.5122 0.0943 0.3976 0.3034 0.0143 0.0000 0.0196 -0.0498 0.185 - 86 6.7314 1.6096 0.3326 0.4403 0.0966 0.3592 0.2741 0.0116 0.0000 0.0223 -0.0411 0.169 - 87 6.9144 1.5372 0.2507 0.3541 0.0988 0.3028 0.2310 0.0083 0.0000 0.0234 -0.0307 0.149 - 88 7.0535 1.4822 0.1746 0.2589 0.1004 0.2299 0.1754 0.0045 0.0000 0.0213 -0.0203 0.129 - 89 7.1471 1.4451 0.1029 0.1579 0.1016 0.1441 0.1099 0.0013 0.0000 0.0152 -0.0112 0.112 - 90 7.1941 1.4265 0.0340 0.0531 0.1022 0.0495 0.0377 -0.0019 0.0000 0.0055 -0.0035 0.103 + 61 0.0047 4.2713 0.0803 1.0500 0.1300 0.3035 0.2317 0.1304 0.0000 -0.0153 -0.0661 0.316 + 62 0.0418 4.2566 0.2392 0.8944 0.1304 0.2725 0.2080 0.0304 0.0000 -0.0145 -0.0579 0.320 + 63 0.1156 4.2274 0.3930 0.8826 0.1305 0.2718 0.2074 0.0236 0.0000 -0.0139 -0.0571 0.317 + 64 0.2254 4.1839 0.5386 0.8794 0.1300 0.2739 0.2090 0.0221 0.0000 -0.0128 -0.0566 0.311 + 65 0.3698 4.1268 0.6730 0.8785 0.1288 0.2775 0.2118 0.0218 0.0000 -0.0115 -0.0560 0.304 + 66 0.5474 4.0565 0.7936 0.8771 0.1267 0.2819 0.2152 0.0217 0.0000 -0.0100 -0.0555 0.296 + 67 0.7617 3.9717 0.9441 0.8756 0.1234 0.2876 0.2195 0.0214 0.0000 -0.0085 -0.0552 0.289 + 68 1.0116 3.8728 1.0344 0.8724 0.1189 0.2940 0.2243 0.0212 0.0000 -0.0070 -0.0551 0.281 + 69 1.2891 3.7630 1.1046 0.8690 0.1132 0.3014 0.2300 0.0212 0.0000 -0.0058 -0.0552 0.275 + 70 1.5912 3.6435 1.1542 0.8647 0.1068 0.3099 0.2365 0.0213 0.0000 -0.0047 -0.0557 0.270 + 71 1.9146 3.5155 1.1831 0.8596 0.1005 0.3193 0.2437 0.0214 0.0000 -0.0038 -0.0565 0.265 + 72 2.2558 3.3805 1.1921 0.8533 0.0948 0.3297 0.2517 0.0216 0.0000 -0.0030 -0.0576 0.262 + 73 2.6109 3.2400 1.1821 0.8471 0.0904 0.3416 0.2607 0.0218 0.0000 -0.0022 -0.0589 0.258 + 74 2.9762 3.0955 1.1548 0.8397 0.0871 0.3545 0.2706 0.0221 0.0000 -0.0015 -0.0604 0.255 + 75 3.3476 2.9485 1.1122 0.8307 0.0848 0.3683 0.2811 0.0222 0.0000 -0.0007 -0.0621 0.253 + 76 3.7210 2.8008 1.0564 0.8198 0.0833 0.3828 0.2921 0.0225 0.0000 0.0001 -0.0638 0.250 + 77 4.0924 2.6538 0.9900 0.8066 0.0824 0.3976 0.3034 0.0224 0.0000 0.0011 -0.0655 0.247 + 78 4.4577 2.5093 0.9155 0.7898 0.0822 0.4119 0.3143 0.0224 0.0000 0.0022 -0.0669 0.243 + 79 4.8128 2.3687 0.8353 0.7688 0.0826 0.4248 0.3242 0.0222 0.0000 0.0036 -0.0679 0.239 + 80 5.1540 2.2338 0.7518 0.7425 0.0836 0.4353 0.3322 0.0218 0.0000 0.0053 -0.0682 0.234 + 81 5.4774 2.1058 0.6671 0.7104 0.0851 0.4420 0.3373 0.0211 0.0000 0.0074 -0.0675 0.228 + 82 5.7795 1.9862 0.5830 0.6715 0.0872 0.4431 0.3382 0.0198 0.0000 0.0099 -0.0655 0.221 + 83 6.0570 1.8764 0.5012 0.6258 0.0895 0.4372 0.3337 0.0185 0.0000 0.0130 -0.0620 0.211 + 84 6.3069 1.7776 0.4225 0.5724 0.0920 0.4224 0.3224 0.0167 0.0000 0.0163 -0.0567 0.199 + 85 6.5264 1.6907 0.3478 0.5115 0.0943 0.3971 0.3030 0.0143 0.0000 0.0196 -0.0497 0.185 + 86 6.7314 1.6096 0.3326 0.4398 0.0967 0.3588 0.2738 0.0117 0.0000 0.0223 -0.0410 0.169 + 87 6.9144 1.5372 0.2507 0.3536 0.0988 0.3023 0.2307 0.0083 0.0000 0.0234 -0.0307 0.148 + 88 7.0535 1.4822 0.1746 0.2588 0.1005 0.2298 0.1753 0.0045 0.0000 0.0213 -0.0203 0.128 + 89 7.1471 1.4451 0.1029 0.1577 0.1016 0.1439 0.1098 0.0013 0.0000 0.0152 -0.0112 0.112 + 90 7.1941 1.4265 0.0340 0.0531 0.1022 0.0494 0.0377 -0.0019 0.0000 0.0055 -0.0035 0.103 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04369 Clsurf = 0.00458 - CYsurf = 0.00708 Cmsurf = -0.21395 - CDsurf = 0.00356 Cnsurf = -0.00394 - CDisurf = 0.00356 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04352 Clsurf = 0.00457 + CYsurf = 0.00706 Cmsurf = -0.21310 + CDsurf = 0.00355 Cnsurf = -0.00392 + CDisurf = 0.00355 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.26641 CDsurf = 0.02144 + CLsurf = 0.26533 CDsurf = 0.02136 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.0570 0.1299 0.3055 0.2332 0.1318 0.0000 -0.0154 0.0665 0.316 - 92 -0.0418 4.2566 0.2392 0.8996 0.1303 0.2740 0.2092 0.0305 0.0000 -0.0145 0.0582 0.320 - 93 -0.1156 4.2274 0.3930 0.8880 0.1304 0.2735 0.2087 0.0238 0.0000 -0.0139 0.0575 0.317 - 94 -0.2254 4.1839 0.5386 0.8847 0.1299 0.2755 0.2103 0.0224 0.0000 -0.0129 0.0569 0.311 - 95 -0.3698 4.1268 0.6730 0.8836 0.1287 0.2791 0.2130 0.0219 0.0000 -0.0115 0.0563 0.304 - 96 -0.5474 4.0565 0.7936 0.8820 0.1266 0.2835 0.2164 0.0217 0.0000 -0.0100 0.0558 0.296 - 97 -0.7617 3.9717 0.9441 0.8803 0.1233 0.2891 0.2207 0.0215 0.0000 -0.0085 0.0554 0.288 - 98 -1.0116 3.8728 1.0344 0.8780 0.1188 0.2958 0.2258 0.0214 0.0000 -0.0070 0.0554 0.281 - 99 -1.2891 3.7630 1.1046 0.8741 0.1131 0.3032 0.2314 0.0214 0.0000 -0.0058 0.0555 0.275 - 100 -1.5912 3.6435 1.1542 0.8696 0.1067 0.3116 0.2378 0.0214 0.0000 -0.0047 0.0560 0.270 - 101 -1.9146 3.5155 1.1831 0.8644 0.1003 0.3211 0.2451 0.0216 0.0000 -0.0037 0.0568 0.265 - 102 -2.2558 3.3805 1.1921 0.8578 0.0947 0.3315 0.2530 0.0216 0.0000 -0.0029 0.0578 0.262 - 103 -2.6109 3.2400 1.1821 0.8514 0.0902 0.3433 0.2620 0.0219 0.0000 -0.0022 0.0592 0.258 - 104 -2.9762 3.0955 1.1548 0.8433 0.0869 0.3561 0.2717 0.0222 0.0000 -0.0014 0.0607 0.255 - 105 -3.3476 2.9485 1.1122 0.8341 0.0847 0.3698 0.2823 0.0222 0.0000 -0.0007 0.0623 0.252 - 106 -3.7210 2.8008 1.0564 0.8230 0.0832 0.3843 0.2933 0.0224 0.0000 0.0001 0.0640 0.250 - 107 -4.0924 2.6538 0.9900 0.8093 0.0823 0.3989 0.3045 0.0225 0.0000 0.0011 0.0657 0.246 - 108 -4.4577 2.5093 0.9155 0.7924 0.0821 0.4132 0.3154 0.0225 0.0000 0.0022 0.0671 0.243 - 109 -4.8128 2.3687 0.8353 0.7708 0.0825 0.4260 0.3251 0.0222 0.0000 0.0036 0.0680 0.239 - 110 -5.1540 2.2338 0.7518 0.7440 0.0835 0.4362 0.3329 0.0218 0.0000 0.0053 0.0683 0.234 - 111 -5.4774 2.1058 0.6671 0.7121 0.0851 0.4430 0.3381 0.0211 0.0000 0.0074 0.0676 0.228 - 112 -5.7795 1.9862 0.5830 0.6728 0.0871 0.4439 0.3388 0.0199 0.0000 0.0100 0.0656 0.221 - 113 -6.0570 1.8764 0.5012 0.6268 0.0894 0.4380 0.3343 0.0185 0.0000 0.0130 0.0621 0.211 - 114 -6.3069 1.7776 0.4225 0.5732 0.0919 0.4230 0.3228 0.0167 0.0000 0.0163 0.0567 0.199 - 115 -6.5264 1.6907 0.3478 0.5122 0.0943 0.3976 0.3034 0.0143 0.0000 0.0196 0.0498 0.185 - 116 -6.7314 1.6096 0.3326 0.4403 0.0966 0.3592 0.2741 0.0116 0.0000 0.0223 0.0411 0.169 - 117 -6.9144 1.5372 0.2507 0.3541 0.0988 0.3027 0.2310 0.0083 0.0000 0.0234 0.0307 0.149 - 118 -7.0535 1.4822 0.1746 0.2589 0.1004 0.2299 0.1754 0.0045 0.0000 0.0213 0.0203 0.129 - 119 -7.1471 1.4451 0.1029 0.1579 0.1016 0.1441 0.1099 0.0013 0.0000 0.0152 0.0112 0.112 - 120 -7.1941 1.4265 0.0340 0.0531 0.1022 0.0495 0.0377 -0.0019 0.0000 0.0055 0.0035 0.103 + 91 -0.0047 4.2713 0.0803 1.0500 0.1300 0.3035 0.2317 0.1304 0.0000 -0.0153 0.0661 0.316 + 92 -0.0418 4.2566 0.2392 0.8944 0.1304 0.2725 0.2080 0.0304 0.0000 -0.0145 0.0579 0.320 + 93 -0.1156 4.2274 0.3930 0.8826 0.1305 0.2718 0.2074 0.0236 0.0000 -0.0139 0.0571 0.317 + 94 -0.2254 4.1839 0.5386 0.8794 0.1300 0.2739 0.2090 0.0221 0.0000 -0.0128 0.0566 0.311 + 95 -0.3698 4.1268 0.6730 0.8785 0.1288 0.2775 0.2118 0.0218 0.0000 -0.0115 0.0560 0.304 + 96 -0.5474 4.0565 0.7936 0.8771 0.1267 0.2819 0.2152 0.0217 0.0000 -0.0100 0.0555 0.296 + 97 -0.7617 3.9717 0.9441 0.8756 0.1234 0.2876 0.2195 0.0214 0.0000 -0.0085 0.0552 0.289 + 98 -1.0116 3.8728 1.0344 0.8724 0.1189 0.2940 0.2243 0.0212 0.0000 -0.0070 0.0551 0.281 + 99 -1.2891 3.7630 1.1046 0.8690 0.1132 0.3014 0.2300 0.0212 0.0000 -0.0058 0.0552 0.275 + 100 -1.5912 3.6435 1.1542 0.8647 0.1068 0.3099 0.2365 0.0213 0.0000 -0.0047 0.0557 0.270 + 101 -1.9146 3.5155 1.1831 0.8596 0.1005 0.3193 0.2437 0.0214 0.0000 -0.0038 0.0565 0.265 + 102 -2.2558 3.3805 1.1921 0.8533 0.0948 0.3297 0.2517 0.0216 0.0000 -0.0030 0.0576 0.262 + 103 -2.6109 3.2400 1.1821 0.8471 0.0904 0.3416 0.2607 0.0218 0.0000 -0.0022 0.0589 0.258 + 104 -2.9762 3.0955 1.1548 0.8397 0.0871 0.3545 0.2706 0.0221 0.0000 -0.0015 0.0604 0.255 + 105 -3.3476 2.9485 1.1122 0.8307 0.0848 0.3683 0.2811 0.0222 0.0000 -0.0007 0.0621 0.253 + 106 -3.7210 2.8008 1.0564 0.8198 0.0833 0.3828 0.2921 0.0225 0.0000 0.0001 0.0638 0.250 + 107 -4.0924 2.6538 0.9900 0.8066 0.0824 0.3976 0.3034 0.0224 0.0000 0.0011 0.0655 0.247 + 108 -4.4577 2.5093 0.9155 0.7898 0.0822 0.4119 0.3143 0.0224 0.0000 0.0022 0.0669 0.243 + 109 -4.8128 2.3687 0.8353 0.7688 0.0826 0.4248 0.3242 0.0222 0.0000 0.0036 0.0679 0.239 + 110 -5.1540 2.2338 0.7518 0.7425 0.0836 0.4353 0.3322 0.0218 0.0000 0.0053 0.0682 0.234 + 111 -5.4774 2.1058 0.6671 0.7104 0.0851 0.4419 0.3373 0.0211 0.0000 0.0074 0.0675 0.228 + 112 -5.7795 1.9862 0.5830 0.6715 0.0872 0.4431 0.3382 0.0198 0.0000 0.0099 0.0655 0.221 + 113 -6.0570 1.8764 0.5012 0.6258 0.0895 0.4372 0.3337 0.0185 0.0000 0.0130 0.0620 0.211 + 114 -6.3069 1.7776 0.4225 0.5724 0.0920 0.4224 0.3224 0.0167 0.0000 0.0163 0.0567 0.199 + 115 -6.5264 1.6907 0.3478 0.5115 0.0943 0.3971 0.3030 0.0143 0.0000 0.0196 0.0497 0.185 + 116 -6.7314 1.6096 0.3326 0.4398 0.0967 0.3588 0.2738 0.0117 0.0000 0.0223 0.0410 0.169 + 117 -6.9144 1.5372 0.2507 0.3536 0.0988 0.3023 0.2307 0.0083 0.0000 0.0234 0.0307 0.148 + 118 -7.0535 1.4822 0.1746 0.2588 0.1005 0.2298 0.1753 0.0045 0.0000 0.0213 0.0203 0.128 + 119 -7.1471 1.4451 0.1029 0.1577 0.1016 0.1439 0.1098 0.0013 0.0000 0.0152 0.0112 0.112 + 120 -7.1941 1.4265 0.0340 0.0531 0.1022 0.0494 0.0377 -0.0019 0.0000 0.0055 0.0035 0.103 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,67 +198,67 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.434 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.443 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.454 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.463 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.465 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.462 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.455 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.437 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.405 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.358 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.315 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.451 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.459 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.461 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.472 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.471 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.468 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.457 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.431 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.402 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.357 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.313 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.298 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.289 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.279 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.267 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.259 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.252 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.241 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.234 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.222 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.199 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.187 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.169 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.147 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.125 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.108 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.290 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.278 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.269 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.262 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.253 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.248 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 + 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.214 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.185 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.171 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.148 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.128 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.110 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.097 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01043 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.06401 + CLsurf = 0.01036 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = 0.06408 CDsurf = -0.00018 Cnsurf = -0.00000 CDisurf = -0.00018 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01051 CDsurf = -0.00018 + CLsurf = 0.01044 CDsurf = -0.00018 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.2373 0.1864 0.1012 0.0094 -0.0034 0.0000 0.0044 0.0003 -0.220 - 152 -1.3090 31.2096 11.6724 0.3383 0.2014 0.0413 0.0110 -0.0010 0.0000 0.0056 0.0007 -0.254 - 153 -0.9350 34.0626 12.7394 0.3674 0.1843 0.0260 0.0109 -0.0001 0.0000 0.0068 0.0014 -0.376 - 154 -0.5610 36.1619 13.5246 0.3850 0.1796 0.0177 0.0106 0.0007 0.0000 0.0074 0.0021 -0.443 - 155 -0.1870 37.5332 14.0374 0.3960 0.1804 0.0121 0.0104 0.0019 0.0000 0.0075 0.0034 -0.473 - 156 0.1870 37.5332 14.0374 0.3960 0.1804 0.0121 0.0104 0.0019 0.0000 0.0075 0.0034 -0.473 - 157 0.5610 36.1619 13.5246 0.3850 0.1796 0.0177 0.0106 0.0007 0.0000 0.0074 0.0021 -0.443 - 158 0.9350 34.0626 12.7394 0.3674 0.1843 0.0260 0.0109 -0.0001 0.0000 0.0068 0.0014 -0.376 - 159 1.3090 31.2096 11.6724 0.3383 0.2014 0.0413 0.0110 -0.0010 0.0000 0.0056 0.0007 -0.254 - 160 1.6830 26.5957 9.9468 0.2373 0.1864 0.1012 0.0094 -0.0034 0.0000 0.0044 0.0003 -0.220 + 151 -1.6830 26.5957 9.9468 0.2354 0.1864 0.1004 0.0093 -0.0034 0.0000 0.0044 0.0003 -0.227 + 152 -1.3090 31.2096 11.6724 0.3358 0.2014 0.0410 0.0110 -0.0010 0.0000 0.0056 0.0007 -0.260 + 153 -0.9350 34.0626 12.7394 0.3649 0.1845 0.0258 0.0108 -0.0001 0.0000 0.0068 0.0014 -0.382 + 154 -0.5610 36.1619 13.5246 0.3825 0.1798 0.0176 0.0106 0.0007 0.0000 0.0074 0.0021 -0.449 + 155 -0.1870 37.5332 14.0374 0.3935 0.1806 0.0120 0.0103 0.0019 0.0000 0.0075 0.0034 -0.479 + 156 0.1870 37.5332 14.0374 0.3935 0.1806 0.0120 0.0103 0.0019 0.0000 0.0075 0.0034 -0.479 + 157 0.5610 36.1619 13.5246 0.3825 0.1798 0.0176 0.0106 0.0007 0.0000 0.0074 0.0021 -0.449 + 158 0.9350 34.0626 12.7394 0.3649 0.1845 0.0258 0.0108 -0.0001 0.0000 0.0068 0.0014 -0.382 + 159 1.3090 31.2096 11.6724 0.3358 0.2014 0.0410 0.0110 -0.0010 0.0000 0.0056 0.0007 -0.260 + 160 1.6830 26.5957 9.9468 0.2354 0.1864 0.1004 0.0093 -0.0034 0.0000 0.0044 0.0003 -0.227 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = -0.00000 + CLsurf = -0.00000 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = 0.00000 CDsurf = 0.00000 Cnsurf = 0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.619 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0002 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.489 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.179 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.391 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.536 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.638 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.733 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.558 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.132 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.366 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.517 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.620 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.717 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_05_06.txt b/regression/scripts/AVL/avl_files/strip_forces_case_05_06.txt index 73437752c9..4938e3dde5 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_05_06.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_05_06.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.58531 Clsurf = -0.11654 - CYsurf = -0.02875 Cmsurf = -0.53941 - CDsurf = 0.02896 Cnsurf = -0.01831 - CDisurf = 0.02896 CDvsurf = 0.00000 + CLsurf = 0.58642 Clsurf = -0.11666 + CYsurf = -0.02853 Cmsurf = -0.53994 + CDsurf = 0.02864 Cnsurf = -0.01832 + CDisurf = 0.02864 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.14364 CDsurf = 0.05653 + CLsurf = 1.14578 CDsurf = 0.05591 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 7.4764 0.2366 0.9429 0.7318 1.3991 0.0000 -0.0609 -0.2486 0.333 - 2 0.1025 7.6885 1.0492 6.4835 0.2366 1.0467 0.8124 0.2481 0.0000 -0.0589 -0.2223 0.322 - 3 0.2837 7.5620 1.7073 6.4028 0.2354 1.0679 0.8288 0.1748 0.0000 -0.0558 -0.2205 0.317 - 4 0.5530 7.3741 2.3052 6.3691 0.2324 1.0946 0.8495 0.1556 0.0000 -0.0507 -0.2199 0.310 - 5 0.9075 7.1267 2.8223 6.3262 0.2256 1.1285 0.8758 0.1443 0.0000 -0.0449 -0.2202 0.301 - 6 1.3432 6.8226 3.2414 6.2660 0.2089 1.1717 0.9094 0.1310 0.0000 -0.0391 -0.2219 0.293 - 7 1.8554 6.4651 3.5491 6.1704 0.1724 1.2216 0.9481 0.1190 0.0000 -0.0342 -0.2253 0.286 - 8 2.4386 6.0582 3.7368 6.0345 0.1366 1.2810 0.9942 0.0977 0.0000 -0.0307 -0.2311 0.281 - 9 3.0862 5.6062 3.8005 5.8463 0.1212 1.3468 1.0453 0.0773 0.0000 -0.0289 -0.2394 0.278 - 10 3.7613 5.1351 3.4440 5.6192 0.1091 1.4167 1.0994 0.0663 0.0000 -0.0289 -0.2500 0.276 - 11 4.4532 4.6522 3.3149 5.3943 0.0933 1.5073 1.1698 0.0433 0.0000 -0.0301 -0.2645 0.276 - 12 5.1831 4.1429 3.0930 5.1375 0.0678 1.6184 1.2560 0.0182 0.0000 -0.0306 -0.2816 0.274 - 13 6.0123 3.7903 3.4706 4.8258 0.0494 1.5875 1.2917 0.0065 0.0000 -0.0225 -0.3100 0.267 - 14 6.9353 3.6075 3.3775 4.5933 0.0458 1.5873 1.2915 0.0081 0.0000 -0.0216 -0.3093 0.267 - 15 7.8737 3.4215 3.2389 4.3775 0.0397 1.5954 1.2981 0.0061 0.0000 -0.0208 -0.3100 0.266 - 16 8.8172 3.2345 3.0619 4.1672 0.0357 1.6071 1.3077 0.0034 0.0000 -0.0200 -0.3114 0.265 - 17 9.7556 3.0486 2.8543 3.9560 0.0350 1.6194 1.3176 0.0004 0.0000 -0.0193 -0.3129 0.265 - 18 10.6786 2.8657 2.6240 3.7437 0.0363 1.6309 1.3270 -0.0026 0.0000 -0.0185 -0.3141 0.264 - 19 11.5760 2.6879 2.3787 3.5298 0.0392 1.6401 1.3345 -0.0055 0.0000 -0.0175 -0.3148 0.263 - 20 12.4328 2.5181 2.1010 3.3142 0.0434 1.6444 1.3380 -0.0083 0.0000 -0.0159 -0.3141 0.262 - 21 13.2400 2.3582 1.8520 3.0952 0.0493 1.6404 1.3348 -0.0108 0.0000 -0.0136 -0.3112 0.260 - 22 13.9941 2.2087 1.6074 2.8682 0.0573 1.6234 1.3210 -0.0131 0.0000 -0.0100 -0.3049 0.258 - 23 14.6868 2.0715 1.3716 2.6268 0.0677 1.5858 1.2903 -0.0148 0.0000 -0.0047 -0.2932 0.254 - 24 15.3105 1.9479 1.1479 2.3628 0.0800 1.5173 1.2346 -0.0159 0.0000 0.0024 -0.2745 0.248 - 25 15.8583 1.8393 0.9381 2.0652 0.0930 1.4043 1.1427 -0.0140 0.0000 0.0083 -0.2486 0.243 - 26 16.3244 1.7470 0.7427 1.7289 0.1064 1.2351 1.0050 -0.0001 0.0000 0.0036 -0.2225 0.246 - 27 16.6722 1.4928 0.4131 1.3687 0.1204 3.0903 0.9444 -0.0729 0.0000 -0.0020 -0.1185 0.252 - 28 16.9098 1.1466 0.2292 1.0063 0.1378 3.0002 0.9169 -0.1413 0.0000 0.0370 -0.0959 0.210 - 29 17.0696 0.9138 0.1104 0.6173 0.1502 2.3612 0.7216 -0.1962 0.0000 0.0698 -0.0552 0.153 - 30 17.1499 0.7967 0.0322 0.2081 0.1562 0.9564 0.2923 -0.1488 0.0000 0.0421 -0.0145 0.106 + 1 0.0114 7.7520 0.3539 7.4993 0.2366 0.9462 0.7343 1.4018 0.0000 -0.0628 -0.2507 0.336 + 2 0.1025 7.6885 1.0491 6.5007 0.2365 1.0497 0.8147 0.2481 0.0000 -0.0603 -0.2239 0.324 + 3 0.2837 7.5620 1.7073 6.4197 0.2355 1.0709 0.8311 0.1747 0.0000 -0.0572 -0.2221 0.319 + 4 0.5530 7.3741 2.3052 6.3852 0.2328 1.0977 0.8519 0.1546 0.0000 -0.0522 -0.2216 0.311 + 5 0.9075 7.1267 2.8223 6.3432 0.2262 1.1323 0.8788 0.1415 0.0000 -0.0464 -0.2219 0.303 + 6 1.3432 6.8226 3.2414 6.2802 0.2096 1.1747 0.9117 0.1300 0.0000 -0.0406 -0.2235 0.295 + 7 1.8554 6.4651 3.5491 6.1770 0.1731 1.2260 0.9516 0.1052 0.0000 -0.0359 -0.2269 0.288 + 8 2.4386 6.0582 3.7368 6.0390 0.1374 1.2829 0.9957 0.0935 0.0000 -0.0322 -0.2325 0.282 + 9 3.0862 5.6062 3.8005 5.8572 0.1224 1.3487 1.0468 0.0797 0.0000 -0.0302 -0.2408 0.279 + 10 3.7613 5.1351 3.4440 5.6444 0.1099 1.4224 1.1039 0.0692 0.0000 -0.0297 -0.2516 0.277 + 11 4.4532 4.6522 3.3149 5.4618 0.0932 1.5245 1.1831 0.0512 0.0000 -0.0278 -0.2656 0.274 + 12 5.1831 4.1429 3.0930 5.1529 0.0670 1.6237 1.2601 0.0166 0.0000 -0.0284 -0.2805 0.273 + 13 6.0123 3.7903 3.4706 4.8288 0.0488 1.5885 1.2925 0.0066 0.0000 -0.0208 -0.3087 0.266 + 14 6.9353 3.6075 3.3775 4.5947 0.0455 1.5878 1.2920 0.0081 0.0000 -0.0199 -0.3079 0.265 + 15 7.8737 3.4215 3.2389 4.3788 0.0395 1.5958 1.2985 0.0062 0.0000 -0.0189 -0.3084 0.265 + 16 8.8172 3.2345 3.0619 4.1691 0.0356 1.6078 1.3083 0.0034 0.0000 -0.0181 -0.3098 0.264 + 17 9.7556 3.0486 2.8543 3.9576 0.0349 1.6201 1.3182 0.0001 0.0000 -0.0174 -0.3113 0.263 + 18 10.6786 2.8657 2.6239 3.7451 0.0363 1.6316 1.3276 -0.0027 0.0000 -0.0166 -0.3125 0.262 + 19 11.5760 2.6879 2.3787 3.5309 0.0391 1.6406 1.3349 -0.0056 0.0000 -0.0155 -0.3132 0.262 + 20 12.4328 2.5181 2.1010 3.3152 0.0433 1.6449 1.3384 -0.0085 0.0000 -0.0140 -0.3125 0.260 + 21 13.2400 2.3582 1.8520 3.0960 0.0492 1.6408 1.3351 -0.0109 0.0000 -0.0116 -0.3096 0.259 + 22 13.9941 2.2087 1.6074 2.8689 0.0572 1.6239 1.3213 -0.0132 0.0000 -0.0081 -0.3032 0.256 + 23 14.6868 2.0715 1.3716 2.6271 0.0677 1.5860 1.2905 -0.0150 0.0000 -0.0027 -0.2916 0.252 + 24 15.3105 1.9479 1.1479 2.3629 0.0799 1.5174 1.2347 -0.0161 0.0000 0.0043 -0.2727 0.246 + 25 15.8583 1.8393 0.9381 2.0653 0.0929 1.4044 1.1427 -0.0141 0.0000 0.0103 -0.2469 0.241 + 26 16.3244 1.7470 0.7427 1.7283 0.1060 1.2347 1.0047 -0.0003 0.0000 0.0055 -0.2207 0.245 + 27 16.6722 1.4928 0.4131 1.3682 0.1200 3.0895 0.9442 -0.0735 0.0000 -0.0004 -0.1178 0.250 + 28 16.9098 1.1466 0.2292 1.0060 0.1377 2.9995 0.9167 -0.1417 0.0000 0.0382 -0.0953 0.208 + 29 17.0696 0.9138 0.1104 0.6172 0.1503 2.3613 0.7216 -0.1968 0.0000 0.0706 -0.0548 0.152 + 30 17.1499 0.7967 0.0322 0.2082 0.1569 0.9571 0.2925 -0.1496 0.0000 0.0423 -0.0144 0.105 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.58531 Clsurf = 0.11654 - CYsurf = 0.02875 Cmsurf = -0.53941 - CDsurf = 0.02896 Cnsurf = 0.01831 - CDisurf = 0.02896 CDvsurf = 0.00000 + CLsurf = 0.58642 Clsurf = 0.11666 + CYsurf = 0.02853 Cmsurf = -0.53994 + CDsurf = 0.02864 Cnsurf = 0.01832 + CDisurf = 0.02864 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.14363 CDsurf = 0.05653 + CLsurf = 1.14578 CDsurf = 0.05591 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 7.4764 0.2369 0.9429 0.7318 1.3993 0.0000 -0.0609 0.2486 0.333 - 32 -0.1025 7.6885 1.0492 6.4835 0.2366 1.0467 0.8124 0.2481 0.0000 -0.0589 0.2223 0.322 - 33 -0.2837 7.5620 1.7073 6.4028 0.2354 1.0679 0.8288 0.1748 0.0000 -0.0558 0.2205 0.317 - 34 -0.5530 7.3741 2.3052 6.3691 0.2324 1.0946 0.8495 0.1556 0.0000 -0.0507 0.2199 0.310 - 35 -0.9075 7.1267 2.8223 6.3261 0.2256 1.1285 0.8758 0.1443 0.0000 -0.0449 0.2202 0.301 - 36 -1.3432 6.8226 3.2414 6.2660 0.2089 1.1717 0.9094 0.1310 0.0000 -0.0391 0.2219 0.293 - 37 -1.8554 6.4651 3.5491 6.1704 0.1724 1.2216 0.9481 0.1190 0.0000 -0.0342 0.2253 0.286 - 38 -2.4386 6.0582 3.7368 6.0344 0.1366 1.2809 0.9942 0.0977 0.0000 -0.0307 0.2311 0.281 - 39 -3.0862 5.6062 3.8005 5.8463 0.1212 1.3468 1.0453 0.0773 0.0000 -0.0289 0.2394 0.278 - 40 -3.7613 5.1351 3.4440 5.6191 0.1091 1.4167 1.0994 0.0663 0.0000 -0.0289 0.2499 0.276 - 41 -4.4532 4.6522 3.3149 5.3943 0.0933 1.5073 1.1697 0.0433 0.0000 -0.0301 0.2645 0.276 - 42 -5.1831 4.1429 3.0930 5.1375 0.0678 1.6184 1.2560 0.0182 0.0000 -0.0306 0.2816 0.274 - 43 -6.0123 3.7903 3.4706 4.8258 0.0494 1.5875 1.2917 0.0065 0.0000 -0.0225 0.3100 0.267 - 44 -6.9353 3.6075 3.3775 4.5933 0.0458 1.5873 1.2915 0.0081 0.0000 -0.0216 0.3093 0.267 - 45 -7.8737 3.4215 3.2389 4.3775 0.0397 1.5954 1.2981 0.0061 0.0000 -0.0208 0.3100 0.266 - 46 -8.8172 3.2345 3.0619 4.1672 0.0357 1.6071 1.3077 0.0034 0.0000 -0.0200 0.3114 0.265 - 47 -9.7556 3.0486 2.8543 3.9559 0.0350 1.6193 1.3176 0.0004 0.0000 -0.0193 0.3128 0.265 - 48 -10.6786 2.8657 2.6240 3.7437 0.0363 1.6309 1.3270 -0.0026 0.0000 -0.0185 0.3141 0.264 - 49 -11.5760 2.6879 2.3787 3.5298 0.0392 1.6401 1.3345 -0.0055 0.0000 -0.0175 0.3148 0.263 - 50 -12.4328 2.5181 2.1010 3.3142 0.0434 1.6443 1.3380 -0.0083 0.0000 -0.0159 0.3141 0.262 - 51 -13.2400 2.3582 1.8520 3.0952 0.0493 1.6404 1.3348 -0.0108 0.0000 -0.0136 0.3112 0.260 - 52 -13.9941 2.2087 1.6074 2.8682 0.0573 1.6234 1.3210 -0.0131 0.0000 -0.0100 0.3049 0.258 - 53 -14.6868 2.0715 1.3716 2.6268 0.0677 1.5858 1.2903 -0.0148 0.0000 -0.0047 0.2932 0.254 - 54 -15.3105 1.9479 1.1479 2.3628 0.0800 1.5172 1.2346 -0.0159 0.0000 0.0024 0.2745 0.248 - 55 -15.8583 1.8393 0.9381 2.0652 0.0930 1.4043 1.1427 -0.0140 0.0000 0.0083 0.2486 0.243 - 56 -16.3244 1.7470 0.7427 1.7288 0.1064 1.2351 1.0049 -0.0001 0.0000 0.0036 0.2225 0.246 - 57 -16.6722 1.4928 0.4131 1.3687 0.1204 3.0903 0.9444 -0.0729 0.0000 -0.0020 0.1185 0.252 - 58 -16.9098 1.1466 0.2292 1.0063 0.1378 3.0001 0.9169 -0.1413 0.0000 0.0370 0.0959 0.210 - 59 -17.0696 0.9138 0.1104 0.6173 0.1502 2.3612 0.7216 -0.1962 0.0000 0.0698 0.0552 0.153 - 60 -17.1499 0.7967 0.0322 0.2081 0.1562 0.9564 0.2923 -0.1488 0.0000 0.0421 0.0145 0.106 + 31 -0.0114 7.7520 0.3539 7.4993 0.2366 0.9462 0.7343 1.4018 0.0000 -0.0628 0.2507 0.336 + 32 -0.1025 7.6885 1.0491 6.5007 0.2365 1.0497 0.8147 0.2481 0.0000 -0.0603 0.2239 0.324 + 33 -0.2837 7.5620 1.7073 6.4197 0.2355 1.0709 0.8311 0.1747 0.0000 -0.0572 0.2221 0.319 + 34 -0.5530 7.3741 2.3052 6.3852 0.2328 1.0977 0.8519 0.1546 0.0000 -0.0522 0.2216 0.311 + 35 -0.9075 7.1267 2.8223 6.3432 0.2262 1.1323 0.8788 0.1415 0.0000 -0.0464 0.2219 0.303 + 36 -1.3432 6.8226 3.2414 6.2802 0.2096 1.1747 0.9117 0.1300 0.0000 -0.0406 0.2235 0.295 + 37 -1.8554 6.4651 3.5491 6.1770 0.1731 1.2260 0.9516 0.1052 0.0000 -0.0359 0.2269 0.288 + 38 -2.4386 6.0582 3.7368 6.0390 0.1374 1.2829 0.9957 0.0935 0.0000 -0.0322 0.2325 0.282 + 39 -3.0862 5.6062 3.8005 5.8572 0.1224 1.3487 1.0468 0.0797 0.0000 -0.0302 0.2408 0.279 + 40 -3.7613 5.1351 3.4440 5.6444 0.1099 1.4224 1.1039 0.0692 0.0000 -0.0297 0.2516 0.277 + 41 -4.4532 4.6522 3.3149 5.4618 0.0932 1.5245 1.1831 0.0512 0.0000 -0.0278 0.2656 0.274 + 42 -5.1831 4.1429 3.0930 5.1529 0.0670 1.6237 1.2601 0.0166 0.0000 -0.0284 0.2805 0.273 + 43 -6.0123 3.7903 3.4706 4.8288 0.0488 1.5885 1.2925 0.0066 0.0000 -0.0208 0.3087 0.266 + 44 -6.9353 3.6075 3.3775 4.5947 0.0455 1.5878 1.2920 0.0081 0.0000 -0.0199 0.3079 0.265 + 45 -7.8737 3.4215 3.2389 4.3788 0.0395 1.5958 1.2985 0.0062 0.0000 -0.0189 0.3084 0.265 + 46 -8.8172 3.2345 3.0619 4.1691 0.0356 1.6078 1.3083 0.0034 0.0000 -0.0181 0.3098 0.264 + 47 -9.7556 3.0486 2.8543 3.9576 0.0349 1.6201 1.3182 0.0001 0.0000 -0.0174 0.3113 0.263 + 48 -10.6786 2.8657 2.6239 3.7451 0.0363 1.6316 1.3276 -0.0027 0.0000 -0.0166 0.3125 0.262 + 49 -11.5760 2.6879 2.3787 3.5309 0.0391 1.6406 1.3349 -0.0056 0.0000 -0.0155 0.3132 0.262 + 50 -12.4328 2.5181 2.1010 3.3152 0.0433 1.6449 1.3384 -0.0085 0.0000 -0.0140 0.3125 0.260 + 51 -13.2400 2.3582 1.8520 3.0960 0.0492 1.6408 1.3351 -0.0109 0.0000 -0.0116 0.3096 0.259 + 52 -13.9941 2.2087 1.6074 2.8689 0.0572 1.6239 1.3213 -0.0132 0.0000 -0.0081 0.3032 0.256 + 53 -14.6868 2.0715 1.3716 2.6271 0.0677 1.5860 1.2905 -0.0150 0.0000 -0.0027 0.2916 0.252 + 54 -15.3105 1.9479 1.1479 2.3629 0.0799 1.5174 1.2347 -0.0161 0.0000 0.0043 0.2727 0.246 + 55 -15.8583 1.8393 0.9381 2.0653 0.0929 1.4044 1.1427 -0.0141 0.0000 0.0103 0.2469 0.241 + 56 -16.3244 1.7470 0.7427 1.7283 0.1060 1.2347 1.0047 -0.0003 0.0000 0.0055 0.2207 0.245 + 57 -16.6722 1.4928 0.4131 1.3682 0.1200 3.0895 0.9442 -0.0735 0.0000 -0.0004 0.1178 0.250 + 58 -16.9098 1.1466 0.2292 1.0060 0.1377 2.9995 0.9167 -0.1417 0.0000 0.0382 0.0953 0.208 + 59 -17.0696 0.9138 0.1104 0.6172 0.1503 2.3613 0.7216 -0.1968 0.0000 0.0706 0.0548 0.152 + 60 -17.1499 0.7967 0.0322 0.2082 0.1569 0.9571 0.2925 -0.1496 0.0000 0.0423 0.0144 0.105 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06849 Clsurf = -0.00707 - CYsurf = -0.01117 Cmsurf = -0.33642 - CDsurf = 0.00759 Cnsurf = 0.00596 - CDisurf = 0.00759 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06831 Clsurf = -0.00705 + CYsurf = -0.01114 Cmsurf = -0.33555 + CDsurf = 0.00757 Cnsurf = 0.00595 + CDisurf = 0.00757 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.41767 CDsurf = 0.04568 + CLsurf = 0.41657 CDsurf = 0.04555 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.8789 0.1799 0.5084 0.3865 0.3401 0.0000 -0.0239 -0.1162 0.312 - 62 0.0418 4.2566 0.2392 1.4655 0.1806 0.4431 0.3368 0.0721 0.0000 -0.0222 -0.0946 0.316 - 63 0.1156 4.2274 0.3930 1.4349 0.1809 0.4408 0.3351 0.0541 0.0000 -0.0212 -0.0927 0.313 - 64 0.2254 4.1839 0.5386 1.4258 0.1804 0.4435 0.3371 0.0503 0.0000 -0.0194 -0.0915 0.308 - 65 0.3698 4.1268 0.6730 1.4226 0.1788 0.4491 0.3414 0.0488 0.0000 -0.0172 -0.0906 0.300 - 66 0.5474 4.0565 0.7936 1.4186 0.1759 0.4559 0.3465 0.0482 0.0000 -0.0147 -0.0897 0.292 - 67 0.7617 3.9717 0.9441 1.4146 0.1714 0.4647 0.3532 0.0473 0.0000 -0.0122 -0.0890 0.285 - 68 1.0116 3.8728 1.0344 1.4099 0.1650 0.4754 0.3613 0.0468 0.0000 -0.0099 -0.0888 0.277 - 69 1.2891 3.7630 1.1046 1.4012 0.1569 0.4866 0.3698 0.0465 0.0000 -0.0078 -0.0890 0.271 - 70 1.5912 3.6435 1.1542 1.3916 0.1476 0.4995 0.3796 0.0461 0.0000 -0.0060 -0.0896 0.266 - 71 1.9146 3.5155 1.1831 1.3806 0.1384 0.5138 0.3905 0.0463 0.0000 -0.0045 -0.0907 0.261 - 72 2.2558 3.3805 1.1921 1.3656 0.1303 0.5289 0.4020 0.0460 0.0000 -0.0032 -0.0921 0.258 - 73 2.6109 3.2400 1.1821 1.3509 0.1240 0.5462 0.4152 0.0463 0.0000 -0.0019 -0.0939 0.255 - 74 2.9762 3.0955 1.1548 1.3326 0.1196 0.5642 0.4288 0.0466 0.0000 -0.0008 -0.0960 0.252 - 75 3.3476 2.9485 1.1122 1.3118 0.1166 0.5835 0.4435 0.0464 0.0000 0.0004 -0.0982 0.249 - 76 3.7210 2.8008 1.0564 1.2881 0.1148 0.6035 0.4587 0.0466 0.0000 0.0016 -0.1005 0.247 - 77 4.0924 2.6538 0.9900 1.2601 0.1140 0.6235 0.4739 0.0465 0.0000 0.0030 -0.1026 0.244 - 78 4.4577 2.5093 0.9155 1.2277 0.1141 0.6428 0.4886 0.0463 0.0000 0.0047 -0.1044 0.240 - 79 4.8128 2.3687 0.8353 1.1881 0.1149 0.6594 0.5012 0.0454 0.0000 0.0067 -0.1055 0.237 - 80 5.1540 2.2338 0.7518 1.1411 0.1166 0.6721 0.5108 0.0443 0.0000 0.0091 -0.1055 0.232 - 81 5.4774 2.1058 0.6671 1.0877 0.1191 0.6800 0.5169 0.0428 0.0000 0.0123 -0.1042 0.226 - 82 5.7795 1.9862 0.5830 1.0233 0.1222 0.6788 0.5160 0.0400 0.0000 0.0160 -0.1007 0.219 - 83 6.0570 1.8764 0.5012 0.9504 0.1258 0.6679 0.5077 0.0369 0.0000 0.0205 -0.0951 0.210 - 84 6.3069 1.7776 0.4225 0.8665 0.1296 0.6434 0.4891 0.0332 0.0000 0.0254 -0.0868 0.198 - 85 6.5264 1.6907 0.3478 0.7724 0.1332 0.6037 0.4588 0.0282 0.0000 0.0301 -0.0761 0.184 - 86 6.7314 1.6096 0.3326 0.6626 0.1367 0.5446 0.4139 0.0227 0.0000 0.0341 -0.0628 0.168 - 87 6.9144 1.5372 0.2507 0.5321 0.1399 0.4587 0.3486 0.0158 0.0000 0.0356 -0.0470 0.148 - 88 7.0535 1.4822 0.1746 0.3884 0.1424 0.3482 0.2646 0.0080 0.0000 0.0323 -0.0312 0.128 - 89 7.1471 1.4451 0.1029 0.2367 0.1442 0.2185 0.1660 0.0016 0.0000 0.0230 -0.0172 0.112 - 90 7.1941 1.4265 0.0340 0.0796 0.1451 0.0757 0.0575 -0.0047 0.0000 0.0084 -0.0054 0.105 + 61 0.0047 4.2713 0.0803 1.8707 0.1800 0.5063 0.3849 0.3378 0.0000 -0.0239 -0.1157 0.312 + 62 0.0418 4.2566 0.2392 1.4605 0.1807 0.4416 0.3357 0.0719 0.0000 -0.0221 -0.0942 0.316 + 63 0.1156 4.2274 0.3930 1.4291 0.1810 0.4390 0.3337 0.0537 0.0000 -0.0211 -0.0923 0.313 + 64 0.2254 4.1839 0.5386 1.4201 0.1805 0.4418 0.3358 0.0497 0.0000 -0.0194 -0.0912 0.308 + 65 0.3698 4.1268 0.6730 1.4176 0.1789 0.4475 0.3402 0.0486 0.0000 -0.0171 -0.0903 0.300 + 66 0.5474 4.0565 0.7936 1.4139 0.1760 0.4544 0.3454 0.0481 0.0000 -0.0147 -0.0894 0.292 + 67 0.7617 3.9717 0.9441 1.4105 0.1715 0.4634 0.3522 0.0471 0.0000 -0.0122 -0.0888 0.285 + 68 1.0116 3.8728 1.0344 1.4032 0.1651 0.4732 0.3597 0.0464 0.0000 -0.0099 -0.0884 0.277 + 69 1.2891 3.7630 1.1046 1.3958 0.1570 0.4847 0.3684 0.0462 0.0000 -0.0078 -0.0886 0.271 + 70 1.5912 3.6435 1.1542 1.3867 0.1478 0.4977 0.3783 0.0461 0.0000 -0.0060 -0.0893 0.266 + 71 1.9146 3.5155 1.1831 1.3752 0.1385 0.5118 0.3890 0.0460 0.0000 -0.0045 -0.0904 0.262 + 72 2.2558 3.3805 1.1921 1.3609 0.1304 0.5271 0.4006 0.0460 0.0000 -0.0032 -0.0918 0.258 + 73 2.6109 3.2400 1.1821 1.3464 0.1242 0.5443 0.4137 0.0463 0.0000 -0.0019 -0.0937 0.255 + 74 2.9762 3.0955 1.1548 1.3293 0.1197 0.5628 0.4278 0.0466 0.0000 -0.0008 -0.0958 0.252 + 75 3.3476 2.9485 1.1122 1.3087 0.1167 0.5821 0.4424 0.0465 0.0000 0.0003 -0.0980 0.249 + 76 3.7210 2.8008 1.0564 1.2849 0.1149 0.6019 0.4575 0.0467 0.0000 0.0016 -0.1003 0.247 + 77 4.0924 2.6538 0.9900 1.2574 0.1141 0.6221 0.4729 0.0463 0.0000 0.0030 -0.1024 0.244 + 78 4.4577 2.5093 0.9155 1.2248 0.1141 0.6413 0.4874 0.0461 0.0000 0.0046 -0.1042 0.240 + 79 4.8128 2.3687 0.8353 1.1860 0.1150 0.6582 0.5003 0.0455 0.0000 0.0067 -0.1053 0.237 + 80 5.1540 2.2338 0.7518 1.1400 0.1167 0.6714 0.5103 0.0443 0.0000 0.0091 -0.1054 0.232 + 81 5.4774 2.1058 0.6671 1.0858 0.1191 0.6788 0.5160 0.0427 0.0000 0.0122 -0.1040 0.226 + 82 5.7795 1.9862 0.5830 1.0221 0.1223 0.6781 0.5154 0.0398 0.0000 0.0160 -0.1006 0.219 + 83 6.0570 1.8764 0.5012 0.9493 0.1259 0.6671 0.5071 0.0371 0.0000 0.0205 -0.0950 0.210 + 84 6.3069 1.7776 0.4225 0.8658 0.1296 0.6429 0.4886 0.0332 0.0000 0.0254 -0.0867 0.198 + 85 6.5264 1.6907 0.3478 0.7718 0.1332 0.6032 0.4585 0.0281 0.0000 0.0301 -0.0760 0.184 + 86 6.7314 1.6096 0.3326 0.6622 0.1367 0.5443 0.4137 0.0227 0.0000 0.0341 -0.0628 0.168 + 87 6.9144 1.5372 0.2507 0.5314 0.1400 0.4582 0.3482 0.0157 0.0000 0.0356 -0.0470 0.148 + 88 7.0535 1.4822 0.1746 0.3885 0.1425 0.3483 0.2647 0.0081 0.0000 0.0323 -0.0312 0.128 + 89 7.1471 1.4451 0.1029 0.2365 0.1442 0.2183 0.1659 0.0016 0.0000 0.0229 -0.0172 0.112 + 90 7.1941 1.4265 0.0340 0.0796 0.1451 0.0756 0.0575 -0.0046 0.0000 0.0084 -0.0054 0.105 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.06849 Clsurf = 0.00707 - CYsurf = 0.01117 Cmsurf = -0.33642 - CDsurf = 0.00759 Cnsurf = -0.00596 - CDisurf = 0.00759 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.06831 Clsurf = 0.00705 + CYsurf = 0.01114 Cmsurf = -0.33555 + CDsurf = 0.00757 Cnsurf = -0.00595 + CDisurf = 0.00757 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.41766 CDsurf = 0.04568 + CLsurf = 0.41656 CDsurf = 0.04555 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.8789 0.1799 0.5084 0.3865 0.3401 0.0000 -0.0239 0.1162 0.312 - 92 -0.0418 4.2566 0.2392 1.4655 0.1806 0.4431 0.3368 0.0721 0.0000 -0.0222 0.0946 0.316 - 93 -0.1156 4.2274 0.3930 1.4349 0.1809 0.4408 0.3351 0.0541 0.0000 -0.0212 0.0927 0.313 - 94 -0.2254 4.1839 0.5386 1.4258 0.1804 0.4435 0.3371 0.0503 0.0000 -0.0194 0.0915 0.308 - 95 -0.3698 4.1268 0.6730 1.4226 0.1788 0.4491 0.3414 0.0488 0.0000 -0.0172 0.0906 0.300 - 96 -0.5474 4.0565 0.7936 1.4186 0.1759 0.4559 0.3465 0.0482 0.0000 -0.0147 0.0897 0.292 - 97 -0.7617 3.9717 0.9441 1.4146 0.1714 0.4647 0.3532 0.0473 0.0000 -0.0122 0.0890 0.285 - 98 -1.0116 3.8728 1.0344 1.4099 0.1650 0.4754 0.3613 0.0468 0.0000 -0.0099 0.0888 0.277 - 99 -1.2891 3.7630 1.1046 1.4012 0.1569 0.4866 0.3698 0.0465 0.0000 -0.0078 0.0890 0.271 - 100 -1.5912 3.6435 1.1542 1.3916 0.1476 0.4995 0.3796 0.0461 0.0000 -0.0060 0.0896 0.266 - 101 -1.9146 3.5155 1.1831 1.3806 0.1384 0.5138 0.3905 0.0463 0.0000 -0.0045 0.0907 0.261 - 102 -2.2558 3.3805 1.1921 1.3656 0.1303 0.5289 0.4020 0.0460 0.0000 -0.0032 0.0921 0.258 - 103 -2.6109 3.2400 1.1821 1.3509 0.1240 0.5462 0.4151 0.0463 0.0000 -0.0019 0.0939 0.255 - 104 -2.9762 3.0955 1.1548 1.3326 0.1196 0.5642 0.4288 0.0466 0.0000 -0.0008 0.0960 0.252 - 105 -3.3476 2.9485 1.1122 1.3118 0.1166 0.5835 0.4435 0.0464 0.0000 0.0004 0.0982 0.249 - 106 -3.7210 2.8008 1.0564 1.2881 0.1148 0.6035 0.4587 0.0466 0.0000 0.0016 0.1005 0.247 - 107 -4.0924 2.6538 0.9900 1.2601 0.1140 0.6234 0.4739 0.0465 0.0000 0.0030 0.1026 0.244 - 108 -4.4577 2.5093 0.9155 1.2277 0.1140 0.6428 0.4886 0.0463 0.0000 0.0047 0.1044 0.240 - 109 -4.8128 2.3687 0.8353 1.1881 0.1149 0.6594 0.5012 0.0454 0.0000 0.0067 0.1055 0.237 - 110 -5.1540 2.2338 0.7518 1.1411 0.1166 0.6720 0.5108 0.0443 0.0000 0.0091 0.1055 0.232 - 111 -5.4774 2.1058 0.6671 1.0876 0.1191 0.6800 0.5168 0.0428 0.0000 0.0123 0.1041 0.226 - 112 -5.7795 1.9862 0.5830 1.0232 0.1222 0.6788 0.5160 0.0400 0.0000 0.0160 0.1007 0.219 - 113 -6.0570 1.8764 0.5012 0.9503 0.1258 0.6679 0.5077 0.0369 0.0000 0.0205 0.0951 0.210 - 114 -6.3069 1.7776 0.4225 0.8665 0.1296 0.6434 0.4891 0.0332 0.0000 0.0254 0.0868 0.198 - 115 -6.5264 1.6907 0.3478 0.7724 0.1332 0.6037 0.4588 0.0282 0.0000 0.0301 0.0761 0.184 - 116 -6.7314 1.6096 0.3326 0.6626 0.1367 0.5446 0.4139 0.0227 0.0000 0.0341 0.0628 0.168 - 117 -6.9144 1.5372 0.2507 0.5321 0.1399 0.4587 0.3486 0.0158 0.0000 0.0356 0.0470 0.148 - 118 -7.0535 1.4822 0.1746 0.3884 0.1424 0.3482 0.2646 0.0080 0.0000 0.0323 0.0312 0.128 - 119 -7.1471 1.4451 0.1029 0.2367 0.1442 0.2185 0.1660 0.0016 0.0000 0.0230 0.0172 0.112 - 120 -7.1941 1.4265 0.0340 0.0796 0.1451 0.0757 0.0575 -0.0047 0.0000 0.0084 0.0054 0.105 + 91 -0.0047 4.2713 0.0803 1.8707 0.1800 0.5063 0.3849 0.3378 0.0000 -0.0239 0.1157 0.312 + 92 -0.0418 4.2566 0.2392 1.4605 0.1807 0.4416 0.3357 0.0719 0.0000 -0.0221 0.0942 0.316 + 93 -0.1156 4.2274 0.3930 1.4291 0.1810 0.4390 0.3337 0.0537 0.0000 -0.0211 0.0923 0.313 + 94 -0.2254 4.1839 0.5386 1.4201 0.1805 0.4418 0.3358 0.0497 0.0000 -0.0194 0.0912 0.308 + 95 -0.3698 4.1268 0.6730 1.4176 0.1789 0.4475 0.3402 0.0486 0.0000 -0.0171 0.0903 0.300 + 96 -0.5474 4.0565 0.7936 1.4139 0.1760 0.4544 0.3454 0.0481 0.0000 -0.0147 0.0894 0.292 + 97 -0.7617 3.9717 0.9441 1.4105 0.1715 0.4634 0.3522 0.0471 0.0000 -0.0122 0.0888 0.285 + 98 -1.0116 3.8728 1.0344 1.4032 0.1651 0.4732 0.3597 0.0464 0.0000 -0.0099 0.0884 0.277 + 99 -1.2891 3.7630 1.1046 1.3958 0.1570 0.4847 0.3684 0.0462 0.0000 -0.0078 0.0886 0.271 + 100 -1.5912 3.6435 1.1542 1.3867 0.1478 0.4977 0.3783 0.0461 0.0000 -0.0060 0.0893 0.266 + 101 -1.9146 3.5155 1.1831 1.3752 0.1385 0.5118 0.3890 0.0460 0.0000 -0.0045 0.0904 0.262 + 102 -2.2558 3.3805 1.1921 1.3609 0.1304 0.5271 0.4006 0.0460 0.0000 -0.0032 0.0918 0.258 + 103 -2.6109 3.2400 1.1821 1.3464 0.1242 0.5443 0.4137 0.0463 0.0000 -0.0019 0.0936 0.255 + 104 -2.9762 3.0955 1.1548 1.3293 0.1197 0.5628 0.4278 0.0466 0.0000 -0.0008 0.0958 0.252 + 105 -3.3476 2.9485 1.1122 1.3087 0.1167 0.5821 0.4424 0.0465 0.0000 0.0003 0.0980 0.249 + 106 -3.7210 2.8008 1.0564 1.2848 0.1149 0.6019 0.4575 0.0467 0.0000 0.0016 0.1003 0.247 + 107 -4.0924 2.6538 0.9900 1.2574 0.1141 0.6221 0.4729 0.0463 0.0000 0.0030 0.1024 0.244 + 108 -4.4577 2.5093 0.9155 1.2248 0.1141 0.6413 0.4874 0.0461 0.0000 0.0046 0.1042 0.240 + 109 -4.8128 2.3687 0.8353 1.1860 0.1150 0.6582 0.5003 0.0455 0.0000 0.0067 0.1053 0.237 + 110 -5.1540 2.2338 0.7518 1.1400 0.1167 0.6714 0.5103 0.0443 0.0000 0.0091 0.1054 0.232 + 111 -5.4774 2.1058 0.6671 1.0858 0.1191 0.6788 0.5160 0.0427 0.0000 0.0122 0.1040 0.226 + 112 -5.7795 1.9862 0.5830 1.0221 0.1223 0.6781 0.5154 0.0398 0.0000 0.0160 0.1006 0.219 + 113 -6.0570 1.8764 0.5012 0.9493 0.1259 0.6671 0.5071 0.0371 0.0000 0.0205 0.0950 0.210 + 114 -6.3069 1.7776 0.4225 0.8658 0.1296 0.6429 0.4886 0.0332 0.0000 0.0254 0.0867 0.198 + 115 -6.5264 1.6907 0.3478 0.7718 0.1332 0.6032 0.4585 0.0281 0.0000 0.0301 0.0760 0.184 + 116 -6.7314 1.6096 0.3326 0.6622 0.1367 0.5443 0.4137 0.0227 0.0000 0.0341 0.0628 0.168 + 117 -6.9144 1.5372 0.2507 0.5314 0.1400 0.4582 0.3482 0.0157 0.0000 0.0356 0.0470 0.148 + 118 -7.0535 1.4822 0.1746 0.3885 0.1425 0.3483 0.2647 0.0081 0.0000 0.0323 0.0312 0.128 + 119 -7.1471 1.4451 0.1029 0.2365 0.1442 0.2183 0.1659 0.0016 0.0000 0.0229 0.0172 0.112 + 120 -7.1941 1.4265 0.0340 0.0796 0.1451 0.0756 0.0575 -0.0046 0.0000 0.0084 0.0054 0.105 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,67 +198,67 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.454 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.464 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.475 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.484 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.485 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.481 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.473 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.451 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.417 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.470 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.477 + 123 0.0000 9.5266 1.4857 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.480 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.491 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.489 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.486 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.474 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.446 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.415 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.366 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.321 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.302 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.291 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.320 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.303 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.292 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.279 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.266 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.236 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.229 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.224 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.216 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.269 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.259 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.250 + 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.225 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.219 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.207 - 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.193 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.180 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.162 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.140 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.118 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.100 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.090 + 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.197 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.179 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.164 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.141 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.102 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.089 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01679 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.09231 - CDsurf = -0.00010 Cnsurf = -0.00000 + CLsurf = 0.01672 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = 0.09238 + CDsurf = -0.00010 Cnsurf = 0.00000 CDisurf = -0.00010 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01693 CDsurf = -0.00010 + CLsurf = 0.01686 CDsurf = -0.00010 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.3904 0.2686 0.1489 0.0159 -0.0059 0.0000 0.0059 0.0003 -0.118 - 152 -1.3090 31.2096 11.6724 0.5458 0.2876 0.0648 0.0181 -0.0017 0.0000 0.0076 0.0008 -0.173 - 153 -0.9350 34.0626 12.7394 0.5853 0.2560 0.0409 0.0174 0.0001 0.0000 0.0096 0.0018 -0.302 - 154 -0.5610 36.1619 13.5246 0.6098 0.2456 0.0278 0.0169 0.0014 0.0000 0.0105 0.0028 -0.373 - 155 -0.1870 37.5332 14.0374 0.6261 0.2451 0.0188 0.0163 0.0037 0.0000 0.0107 0.0045 -0.409 - 156 0.1870 37.5332 14.0374 0.6261 0.2451 0.0188 0.0163 0.0037 0.0000 0.0107 0.0045 -0.409 - 157 0.5610 36.1619 13.5246 0.6098 0.2456 0.0278 0.0169 0.0014 0.0000 0.0105 0.0028 -0.373 - 158 0.9350 34.0626 12.7394 0.5853 0.2560 0.0409 0.0174 0.0001 0.0000 0.0096 0.0018 -0.302 - 159 1.3090 31.2096 11.6724 0.5458 0.2876 0.0648 0.0181 -0.0017 0.0000 0.0076 0.0008 -0.173 - 160 1.6830 26.5957 9.9468 0.3904 0.2686 0.1489 0.0159 -0.0059 0.0000 0.0059 0.0003 -0.118 + 151 -1.6830 26.5957 9.9468 0.3885 0.2686 0.1483 0.0159 -0.0059 0.0000 0.0059 0.0003 -0.121 + 152 -1.3090 31.2096 11.6724 0.5433 0.2876 0.0645 0.0180 -0.0017 0.0000 0.0077 0.0008 -0.176 + 153 -0.9350 34.0626 12.7394 0.5828 0.2561 0.0407 0.0174 0.0000 0.0000 0.0096 0.0018 -0.305 + 154 -0.5610 36.1619 13.5246 0.6072 0.2458 0.0277 0.0168 0.0014 0.0000 0.0105 0.0028 -0.377 + 155 -0.1870 37.5332 14.0374 0.6236 0.2453 0.0187 0.0162 0.0037 0.0000 0.0107 0.0045 -0.413 + 156 0.1870 37.5332 14.0374 0.6236 0.2453 0.0187 0.0162 0.0037 0.0000 0.0107 0.0045 -0.413 + 157 0.5610 36.1619 13.5246 0.6073 0.2458 0.0277 0.0168 0.0014 0.0000 0.0105 0.0028 -0.377 + 158 0.9350 34.0626 12.7394 0.5828 0.2561 0.0407 0.0174 0.0000 0.0000 0.0096 0.0018 -0.305 + 159 1.3090 31.2096 11.6724 0.5433 0.2875 0.0645 0.0180 -0.0017 0.0000 0.0077 0.0008 -0.176 + 160 1.6830 26.5957 9.9468 0.3885 0.2686 0.1483 0.0159 -0.0059 0.0000 0.0059 0.0003 -0.121 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 + CLsurf = 0.00000 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = 0.00000 Cnsurf = 0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.514 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.289 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0003 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.003 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.356 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.556 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.678 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.779 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.055 + 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.334 + 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.539 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.661 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.764 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_06_01.txt b/regression/scripts/AVL/avl_files/strip_forces_case_06_01.txt index 74a7899be2..87c0aed7d5 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_06_01.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_06_01.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.01388 Clsurf = 0.00225 - CYsurf = -0.00019 Cmsurf = -0.00132 - CDsurf = 0.00050 Cnsurf = -0.00015 - CDisurf = 0.00050 CDvsurf = 0.00000 + CLsurf = 0.01484 Clsurf = 0.00215 + CYsurf = -0.00024 Cmsurf = -0.00183 + CDsurf = 0.00052 Cnsurf = -0.00014 + CDisurf = 0.00052 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.02706 CDsurf = 0.00098 + CLsurf = 0.02893 CDsurf = 0.00101 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 0.8440 0.0131 0.1416 0.1101 0.0319 0.0000 -0.0072 -0.0280 0.315 - 2 0.1025 7.6885 1.0492 0.8217 0.0122 0.1379 0.1072 0.0064 0.0000 -0.0072 -0.0276 0.317 - 3 0.2837 7.5620 1.7073 0.8162 0.0105 0.1392 0.1082 0.0046 0.0000 -0.0070 -0.0276 0.315 - 4 0.5530 7.3741 2.3052 0.8051 0.0078 0.1408 0.1094 0.0040 0.0000 -0.0066 -0.0276 0.310 - 5 0.9075 7.1267 2.8223 0.7830 0.0048 0.1416 0.1101 0.0034 0.0000 -0.0063 -0.0275 0.308 - 6 1.3432 6.8226 3.2414 0.7457 0.0048 0.1408 0.1094 0.0025 0.0000 -0.0063 -0.0274 0.308 - 7 1.8554 6.4651 3.5491 0.6899 0.0143 0.1375 0.1068 0.0017 0.0000 -0.0068 -0.0272 0.313 - 8 2.4386 6.0582 3.7368 0.6130 0.0219 0.1303 0.1013 0.0011 0.0000 -0.0078 -0.0269 0.327 - 9 3.0862 5.6062 3.8005 0.5152 0.0146 0.1183 0.0920 0.0002 0.0000 -0.0097 -0.0266 0.356 - 10 3.7613 5.1351 3.4440 0.4066 0.0048 0.1020 0.0792 -0.0001 0.0000 -0.0127 -0.0264 0.410 - 11 4.4532 4.6522 3.3149 0.2928 -0.0035 0.0810 0.0630 -0.0004 0.0000 -0.0171 -0.0267 0.522 - 12 5.1831 4.1429 3.0930 0.1744 -0.0138 0.0542 0.0421 -0.0004 0.0000 -0.0233 -0.0275 0.803 - 13 6.0123 3.7903 3.4706 0.0693 -0.0188 0.0222 0.0183 -0.0002 0.0000 -0.0288 -0.0297 1.824 - 14 6.9353 3.6075 3.3775 -0.0035 -0.0137 -0.0012 -0.0010 -0.0000 0.0000 -0.0303 -0.0268 - 15 7.8737 3.4215 3.2389 -0.0581 -0.0094 -0.0206 -0.0170 0.0001 0.0000 -0.0310 -0.0238 - 16 8.8172 3.2345 3.0619 -0.0994 -0.0069 -0.0373 -0.0307 0.0002 0.0000 -0.0314 -0.0211 -0.770 - 17 9.7556 3.0486 2.8543 -0.1300 -0.0060 -0.0518 -0.0427 0.0003 0.0000 -0.0316 -0.0187 -0.491 - 18 10.6786 2.8657 2.6240 -0.1517 -0.0060 -0.0643 -0.0530 0.0003 0.0000 -0.0318 -0.0166 -0.351 - 19 11.5760 2.6879 2.3787 -0.1658 -0.0064 -0.0749 -0.0617 0.0003 0.0000 -0.0321 -0.0149 -0.269 - 20 12.4328 2.5181 2.1010 -0.1733 -0.0070 -0.0836 -0.0689 0.0003 0.0000 -0.0324 -0.0136 -0.220 - 21 13.2400 2.3582 1.8520 -0.1748 -0.0076 -0.0900 -0.0742 0.0003 0.0000 -0.0328 -0.0128 -0.192 - 22 13.9941 2.2087 1.6074 -0.1706 -0.0082 -0.0938 -0.0773 0.0002 0.0000 -0.0334 -0.0126 -0.182 - 23 14.6868 2.0715 1.3716 -0.1610 -0.0086 -0.0944 -0.0778 0.0001 0.0000 -0.0341 -0.0131 -0.188 - 24 15.3105 1.9479 1.1479 -0.1462 -0.0087 -0.0911 -0.0751 -0.0001 0.0000 -0.0344 -0.0140 -0.208 - 25 15.8583 1.8393 0.9381 -0.1269 -0.0086 -0.0838 -0.0690 -0.0003 0.0000 -0.0334 -0.0145 -0.234 - 26 16.3244 1.7470 0.7427 -0.1039 -0.0081 -0.0723 -0.0595 -0.0005 0.0000 -0.0292 -0.0129 -0.241 - 27 16.6722 1.4928 0.4131 -0.0798 -0.0075 -0.1764 -0.0535 -0.0015 0.0000 -0.0210 -0.0038 -0.143 - 28 16.9098 1.1466 0.2292 -0.0559 -0.0057 -0.1609 -0.0488 -0.0016 0.0000 -0.0212 -0.0044 -0.185 - 29 17.0696 0.9138 0.1104 -0.0328 -0.0039 -0.1186 -0.0360 -0.0022 0.0000 -0.0186 -0.0046 -0.266 - 30 17.1499 0.7967 0.0322 -0.0108 -0.0032 -0.0451 -0.0137 -0.0035 0.0000 -0.0085 -0.0024 -0.370 + 1 0.0114 7.7520 0.3539 0.8658 0.0124 0.1452 0.1129 0.0318 0.0000 -0.0090 -0.0300 0.330 + 2 0.1025 7.6885 1.0491 0.8412 0.0117 0.1412 0.1097 0.0064 0.0000 -0.0088 -0.0294 0.330 + 3 0.2837 7.5620 1.7073 0.8359 0.0103 0.1425 0.1108 0.0046 0.0000 -0.0086 -0.0294 0.327 + 4 0.5530 7.3741 2.3052 0.8253 0.0080 0.1443 0.1121 0.0040 0.0000 -0.0083 -0.0295 0.324 + 5 0.9075 7.1267 2.8223 0.8040 0.0053 0.1454 0.1130 0.0034 0.0000 -0.0080 -0.0295 0.321 + 6 1.3432 6.8226 3.2414 0.7674 0.0055 0.1449 0.1126 0.0028 0.0000 -0.0081 -0.0294 0.322 + 7 1.8554 6.4651 3.5491 0.7116 0.0151 0.1418 0.1102 0.0019 0.0000 -0.0085 -0.0293 0.327 + 8 2.4386 6.0582 3.7368 0.6347 0.0230 0.1349 0.1049 0.0011 0.0000 -0.0095 -0.0290 0.341 + 9 3.0862 5.6062 3.8005 0.5370 0.0164 0.1233 0.0959 0.0003 0.0000 -0.0114 -0.0287 0.369 + 10 3.7613 5.1351 3.4440 0.4261 0.0063 0.1068 0.0830 -0.0002 0.0000 -0.0138 -0.0281 0.416 + 11 4.4532 4.6522 3.3149 0.3050 -0.0036 0.0844 0.0656 -0.0004 0.0000 -0.0171 -0.0273 0.511 + 12 5.1831 4.1429 3.0930 0.1808 -0.0150 0.0562 0.0437 -0.0004 0.0000 -0.0219 -0.0267 0.752 + 13 6.0123 3.7903 3.4706 0.0743 -0.0194 0.0238 0.0196 -0.0003 0.0000 -0.0268 -0.0281 1.615 + 14 6.9353 3.6075 3.3775 0.0005 -0.0140 0.0002 0.0001 -0.0001 0.0000 -0.0280 -0.0249 + 15 7.8737 3.4215 3.2389 -0.0548 -0.0096 -0.0195 -0.0160 0.0001 0.0000 -0.0285 -0.0219 + 16 8.8172 3.2345 3.0619 -0.0967 -0.0070 -0.0363 -0.0299 0.0002 0.0000 -0.0288 -0.0190 -0.713 + 17 9.7556 3.0486 2.8543 -0.1277 -0.0061 -0.0509 -0.0419 0.0003 0.0000 -0.0290 -0.0166 -0.442 + 18 10.6786 2.8657 2.6239 -0.1498 -0.0061 -0.0635 -0.0523 0.0003 0.0000 -0.0292 -0.0144 -0.308 + 19 11.5760 2.6879 2.3787 -0.1643 -0.0065 -0.0742 -0.0611 0.0003 0.0000 -0.0294 -0.0127 -0.231 + 20 12.4328 2.5181 2.1010 -0.1720 -0.0070 -0.0830 -0.0684 0.0003 0.0000 -0.0297 -0.0113 -0.184 + 21 13.2400 2.3582 1.8520 -0.1738 -0.0076 -0.0895 -0.0737 0.0003 0.0000 -0.0301 -0.0105 -0.158 + 22 13.9941 2.2087 1.6074 -0.1700 -0.0082 -0.0935 -0.0770 0.0002 0.0000 -0.0307 -0.0103 -0.148 + 23 14.6868 2.0715 1.3716 -0.1607 -0.0086 -0.0942 -0.0776 0.0001 0.0000 -0.0313 -0.0108 -0.154 + 24 15.3105 1.9479 1.1479 -0.1463 -0.0088 -0.0912 -0.0751 -0.0000 0.0000 -0.0317 -0.0116 -0.172 + 25 15.8583 1.8393 0.9381 -0.1274 -0.0087 -0.0842 -0.0693 -0.0002 0.0000 -0.0307 -0.0120 -0.193 + 26 16.3244 1.7470 0.7427 -0.1053 -0.0088 -0.0732 -0.0603 -0.0004 0.0000 -0.0265 -0.0103 -0.190 + 27 16.6722 1.4928 0.4131 -0.0810 -0.0081 -0.1791 -0.0544 -0.0014 0.0000 -0.0189 -0.0027 -0.097 + 28 16.9098 1.1466 0.2292 -0.0567 -0.0060 -0.1632 -0.0495 -0.0016 0.0000 -0.0194 -0.0035 -0.142 + 29 17.0696 0.9138 0.1104 -0.0332 -0.0041 -0.1200 -0.0364 -0.0021 0.0000 -0.0173 -0.0040 -0.226 + 30 17.1499 0.7967 0.0322 -0.0108 -0.0025 -0.0452 -0.0137 -0.0032 0.0000 -0.0081 -0.0022 -0.339 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.01388 Clsurf = -0.00225 - CYsurf = 0.00019 Cmsurf = -0.00132 - CDsurf = 0.00050 Cnsurf = 0.00015 - CDisurf = 0.00050 CDvsurf = 0.00000 + CLsurf = 0.01484 Clsurf = -0.00215 + CYsurf = 0.00024 Cmsurf = -0.00183 + CDsurf = 0.00052 Cnsurf = 0.00014 + CDisurf = 0.00052 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.02706 CDsurf = 0.00098 + CLsurf = 0.02893 CDsurf = 0.00101 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 0.8440 0.0129 0.1416 0.1101 0.0319 0.0000 -0.0072 0.0280 0.315 - 32 -0.1025 7.6885 1.0492 0.8216 0.0122 0.1379 0.1072 0.0064 0.0000 -0.0072 0.0276 0.317 - 33 -0.2837 7.5620 1.7073 0.8162 0.0104 0.1392 0.1082 0.0046 0.0000 -0.0070 0.0276 0.315 - 34 -0.5530 7.3741 2.3052 0.8051 0.0078 0.1408 0.1094 0.0040 0.0000 -0.0066 0.0276 0.310 - 35 -0.9075 7.1267 2.8223 0.7830 0.0048 0.1416 0.1101 0.0034 0.0000 -0.0063 0.0275 0.308 - 36 -1.3432 6.8226 3.2414 0.7457 0.0048 0.1408 0.1094 0.0025 0.0000 -0.0063 0.0274 0.308 - 37 -1.8554 6.4651 3.5491 0.6898 0.0143 0.1375 0.1068 0.0017 0.0000 -0.0068 0.0272 0.313 - 38 -2.4386 6.0582 3.7368 0.6130 0.0219 0.1303 0.1013 0.0011 0.0000 -0.0078 0.0269 0.327 - 39 -3.0862 5.6062 3.8005 0.5152 0.0146 0.1183 0.0920 0.0002 0.0000 -0.0097 0.0266 0.356 - 40 -3.7613 5.1351 3.4440 0.4066 0.0048 0.1020 0.0792 -0.0001 0.0000 -0.0127 0.0264 0.410 - 41 -4.4532 4.6522 3.3149 0.2928 -0.0035 0.0810 0.0630 -0.0004 0.0000 -0.0171 0.0267 0.522 - 42 -5.1831 4.1429 3.0930 0.1744 -0.0138 0.0542 0.0421 -0.0004 0.0000 -0.0233 0.0275 0.803 - 43 -6.0123 3.7903 3.4706 0.0693 -0.0188 0.0222 0.0183 -0.0002 0.0000 -0.0288 0.0297 1.824 - 44 -6.9353 3.6075 3.3775 -0.0035 -0.0137 -0.0012 -0.0010 -0.0000 0.0000 -0.0303 0.0268 - 45 -7.8737 3.4215 3.2389 -0.0581 -0.0094 -0.0206 -0.0170 0.0001 0.0000 -0.0310 0.0238 - 46 -8.8172 3.2345 3.0619 -0.0994 -0.0069 -0.0373 -0.0307 0.0002 0.0000 -0.0314 0.0211 -0.770 - 47 -9.7556 3.0486 2.8543 -0.1300 -0.0060 -0.0518 -0.0427 0.0003 0.0000 -0.0316 0.0187 -0.491 - 48 -10.6786 2.8657 2.6240 -0.1517 -0.0060 -0.0643 -0.0530 0.0003 0.0000 -0.0318 0.0166 -0.351 - 49 -11.5760 2.6879 2.3787 -0.1658 -0.0064 -0.0749 -0.0617 0.0003 0.0000 -0.0321 0.0149 -0.269 - 50 -12.4328 2.5181 2.1010 -0.1733 -0.0070 -0.0836 -0.0689 0.0003 0.0000 -0.0324 0.0136 -0.220 - 51 -13.2400 2.3582 1.8520 -0.1748 -0.0076 -0.0900 -0.0742 0.0003 0.0000 -0.0328 0.0128 -0.192 - 52 -13.9941 2.2087 1.6074 -0.1706 -0.0082 -0.0938 -0.0773 0.0002 0.0000 -0.0334 0.0126 -0.182 - 53 -14.6868 2.0715 1.3716 -0.1610 -0.0086 -0.0944 -0.0778 0.0001 0.0000 -0.0341 0.0131 -0.188 - 54 -15.3105 1.9479 1.1479 -0.1462 -0.0087 -0.0911 -0.0751 -0.0001 0.0000 -0.0344 0.0140 -0.208 - 55 -15.8583 1.8393 0.9381 -0.1268 -0.0086 -0.0838 -0.0690 -0.0003 0.0000 -0.0334 0.0145 -0.234 - 56 -16.3244 1.7470 0.7427 -0.1039 -0.0081 -0.0723 -0.0595 -0.0005 0.0000 -0.0292 0.0129 -0.241 - 57 -16.6722 1.4928 0.4131 -0.0798 -0.0075 -0.1764 -0.0535 -0.0015 0.0000 -0.0210 0.0038 -0.143 - 58 -16.9098 1.1466 0.2292 -0.0559 -0.0057 -0.1609 -0.0488 -0.0016 0.0000 -0.0212 0.0044 -0.185 - 59 -17.0696 0.9138 0.1104 -0.0328 -0.0039 -0.1186 -0.0360 -0.0022 0.0000 -0.0186 0.0046 -0.266 - 60 -17.1499 0.7967 0.0322 -0.0108 -0.0032 -0.0451 -0.0137 -0.0035 0.0000 -0.0085 0.0024 -0.370 + 31 -0.0114 7.7520 0.3539 0.8658 0.0124 0.1452 0.1129 0.0318 0.0000 -0.0090 0.0300 0.330 + 32 -0.1025 7.6885 1.0491 0.8412 0.0117 0.1412 0.1097 0.0064 0.0000 -0.0088 0.0294 0.330 + 33 -0.2837 7.5620 1.7073 0.8359 0.0103 0.1425 0.1108 0.0046 0.0000 -0.0086 0.0294 0.327 + 34 -0.5530 7.3741 2.3052 0.8253 0.0080 0.1443 0.1121 0.0040 0.0000 -0.0083 0.0295 0.324 + 35 -0.9075 7.1267 2.8223 0.8040 0.0053 0.1454 0.1130 0.0034 0.0000 -0.0080 0.0295 0.321 + 36 -1.3432 6.8226 3.2414 0.7674 0.0055 0.1449 0.1126 0.0028 0.0000 -0.0081 0.0294 0.322 + 37 -1.8554 6.4651 3.5491 0.7116 0.0151 0.1418 0.1102 0.0019 0.0000 -0.0085 0.0293 0.327 + 38 -2.4386 6.0582 3.7368 0.6347 0.0230 0.1349 0.1049 0.0011 0.0000 -0.0095 0.0290 0.341 + 39 -3.0862 5.6062 3.8005 0.5370 0.0164 0.1233 0.0959 0.0003 0.0000 -0.0114 0.0287 0.369 + 40 -3.7613 5.1351 3.4440 0.4261 0.0063 0.1068 0.0830 -0.0002 0.0000 -0.0138 0.0281 0.416 + 41 -4.4532 4.6522 3.3149 0.3050 -0.0036 0.0844 0.0656 -0.0004 0.0000 -0.0171 0.0273 0.511 + 42 -5.1831 4.1429 3.0930 0.1808 -0.0150 0.0562 0.0437 -0.0004 0.0000 -0.0219 0.0267 0.752 + 43 -6.0123 3.7903 3.4706 0.0743 -0.0194 0.0238 0.0196 -0.0003 0.0000 -0.0268 0.0281 1.615 + 44 -6.9353 3.6075 3.3775 0.0005 -0.0140 0.0002 0.0001 -0.0001 0.0000 -0.0280 0.0249 + 45 -7.8737 3.4215 3.2389 -0.0548 -0.0096 -0.0195 -0.0160 0.0001 0.0000 -0.0285 0.0219 + 46 -8.8172 3.2345 3.0619 -0.0967 -0.0070 -0.0363 -0.0299 0.0002 0.0000 -0.0288 0.0190 -0.713 + 47 -9.7556 3.0486 2.8543 -0.1277 -0.0061 -0.0509 -0.0419 0.0003 0.0000 -0.0290 0.0166 -0.442 + 48 -10.6786 2.8657 2.6239 -0.1498 -0.0061 -0.0635 -0.0523 0.0003 0.0000 -0.0292 0.0144 -0.308 + 49 -11.5760 2.6879 2.3787 -0.1643 -0.0065 -0.0742 -0.0611 0.0003 0.0000 -0.0294 0.0127 -0.231 + 50 -12.4328 2.5181 2.1010 -0.1720 -0.0070 -0.0830 -0.0684 0.0003 0.0000 -0.0297 0.0113 -0.184 + 51 -13.2400 2.3582 1.8520 -0.1738 -0.0076 -0.0895 -0.0737 0.0003 0.0000 -0.0301 0.0105 -0.158 + 52 -13.9941 2.2087 1.6074 -0.1700 -0.0082 -0.0935 -0.0770 0.0002 0.0000 -0.0307 0.0103 -0.148 + 53 -14.6868 2.0715 1.3716 -0.1607 -0.0086 -0.0942 -0.0776 0.0001 0.0000 -0.0313 0.0108 -0.154 + 54 -15.3105 1.9479 1.1479 -0.1463 -0.0088 -0.0912 -0.0751 -0.0000 0.0000 -0.0317 0.0116 -0.172 + 55 -15.8583 1.8393 0.9381 -0.1274 -0.0087 -0.0842 -0.0693 -0.0002 0.0000 -0.0307 0.0120 -0.193 + 56 -16.3244 1.7470 0.7427 -0.1053 -0.0088 -0.0732 -0.0603 -0.0004 0.0000 -0.0265 0.0103 -0.190 + 57 -16.6722 1.4928 0.4131 -0.0810 -0.0081 -0.1791 -0.0544 -0.0014 0.0000 -0.0189 0.0027 -0.097 + 58 -16.9098 1.1466 0.2292 -0.0567 -0.0060 -0.1632 -0.0495 -0.0016 0.0000 -0.0194 0.0035 -0.142 + 59 -17.0696 0.9138 0.1104 -0.0332 -0.0041 -0.1200 -0.0364 -0.0021 0.0000 -0.0173 0.0040 -0.226 + 60 -17.1499 0.7967 0.0322 -0.0108 -0.0025 -0.0452 -0.0137 -0.0032 0.0000 -0.0081 0.0022 -0.339 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.03886 Clsurf = 0.00383 - CYsurf = 0.00618 Cmsurf = 0.18693 - CDsurf = 0.00029 Cnsurf = -0.00382 - CDisurf = 0.00029 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.03913 Clsurf = 0.00386 + CYsurf = 0.00622 Cmsurf = 0.18821 + CDsurf = 0.00028 Cnsurf = -0.00385 + CDisurf = 0.00028 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.23684 CDsurf = 0.00174 + CLsurf = -0.23849 CDsurf = 0.00169 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.6657 -0.0234 -0.1937 -0.1511 0.1412 0.0000 0.0150 0.0452 0.349 - 62 0.0418 4.2566 0.2392 -0.8680 -0.0240 -0.2609 -0.2035 0.0161 0.0000 0.0165 0.0566 0.331 - 63 0.1156 4.2274 0.3930 -0.8842 -0.0246 -0.2680 -0.2090 0.0071 0.0000 0.0162 0.0574 0.328 - 64 0.2254 4.1839 0.5386 -0.8881 -0.0251 -0.2721 -0.2122 0.0053 0.0000 0.0153 0.0573 0.322 - 65 0.3698 4.1268 0.6730 -0.8901 -0.0254 -0.2765 -0.2157 0.0046 0.0000 0.0139 0.0568 0.314 - 66 0.5474 4.0565 0.7936 -0.8896 -0.0254 -0.2812 -0.2193 0.0042 0.0000 0.0122 0.0562 0.306 - 67 0.7617 3.9717 0.9441 -0.8875 -0.0251 -0.2865 -0.2235 0.0037 0.0000 0.0105 0.0555 0.297 - 68 1.0116 3.8728 1.0344 -0.8840 -0.0241 -0.2927 -0.2283 0.0031 0.0000 0.0087 0.0550 0.288 - 69 1.2891 3.7630 1.1046 -0.8774 -0.0225 -0.2990 -0.2332 0.0026 0.0000 0.0070 0.0546 0.280 - 70 1.5912 3.6435 1.1542 -0.8673 -0.0205 -0.3053 -0.2381 0.0021 0.0000 0.0054 0.0543 0.273 - 71 1.9146 3.5155 1.1831 -0.8542 -0.0184 -0.3117 -0.2431 0.0017 0.0000 0.0040 0.0541 0.266 - 72 2.2558 3.3805 1.1921 -0.8370 -0.0168 -0.3176 -0.2477 0.0012 0.0000 0.0028 0.0541 0.261 - 73 2.6109 3.2400 1.1821 -0.8156 -0.0160 -0.3229 -0.2519 0.0009 0.0000 0.0017 0.0540 0.257 - 74 2.9762 3.0955 1.1548 -0.7902 -0.0160 -0.3275 -0.2554 0.0005 0.0000 0.0007 0.0539 0.253 - 75 3.3476 2.9485 1.1122 -0.7611 -0.0165 -0.3312 -0.2583 0.0002 0.0000 -0.0002 0.0538 0.249 - 76 3.7210 2.8008 1.0564 -0.7285 -0.0173 -0.3337 -0.2603 -0.0000 0.0000 -0.0010 0.0535 0.246 - 77 4.0924 2.6538 0.9900 -0.6931 -0.0183 -0.3351 -0.2613 -0.0003 0.0000 -0.0019 0.0529 0.243 - 78 4.4577 2.5093 0.9155 -0.6551 -0.0194 -0.3350 -0.2613 -0.0005 0.0000 -0.0029 0.0521 0.239 - 79 4.8128 2.3687 0.8353 -0.6154 -0.0205 -0.3333 -0.2600 -0.0007 0.0000 -0.0041 0.0508 0.234 - 80 5.1540 2.2338 0.7518 -0.5733 -0.0217 -0.3293 -0.2568 -0.0009 0.0000 -0.0055 0.0490 0.229 - 81 5.4774 2.1058 0.6671 -0.5296 -0.0228 -0.3227 -0.2517 -0.0011 0.0000 -0.0071 0.0465 0.222 - 82 5.7795 1.9862 0.5830 -0.4842 -0.0240 -0.3128 -0.2440 -0.0014 0.0000 -0.0091 0.0432 0.213 - 83 6.0570 1.8764 0.5012 -0.4374 -0.0251 -0.2992 -0.2333 -0.0017 0.0000 -0.0113 0.0391 0.202 - 84 6.3069 1.7776 0.4225 -0.3888 -0.0261 -0.2807 -0.2189 -0.0020 0.0000 -0.0135 0.0343 0.188 - 85 6.5264 1.6907 0.3478 -0.3386 -0.0270 -0.2571 -0.2005 -0.0024 0.0000 -0.0154 0.0288 0.173 - 86 6.7314 1.6096 0.3326 -0.2843 -0.0278 -0.2268 -0.1768 -0.0026 0.0000 -0.0167 0.0227 0.155 - 87 6.9144 1.5372 0.2507 -0.2238 -0.0285 -0.1870 -0.1458 -0.0029 0.0000 -0.0167 0.0163 0.136 - 88 7.0535 1.4822 0.1746 -0.1614 -0.0290 -0.1398 -0.1090 -0.0030 0.0000 -0.0145 0.0104 0.117 - 89 7.1471 1.4451 0.1029 -0.0974 -0.0294 -0.0866 -0.0676 -0.0027 0.0000 -0.0101 0.0056 0.101 - 90 7.1941 1.4265 0.0340 -0.0326 -0.0295 -0.0294 -0.0229 -0.0023 0.0000 -0.0036 0.0017 0.094 + 61 0.0047 4.2713 0.0803 -0.6689 -0.0232 -0.1946 -0.1518 0.1434 0.0000 0.0151 0.0454 0.349 + 62 0.0418 4.2566 0.2392 -0.8746 -0.0238 -0.2629 -0.2050 0.0163 0.0000 0.0166 0.0570 0.331 + 63 0.1156 4.2274 0.3930 -0.8912 -0.0245 -0.2702 -0.2107 0.0071 0.0000 0.0163 0.0578 0.327 + 64 0.2254 4.1839 0.5386 -0.8950 -0.0250 -0.2742 -0.2139 0.0052 0.0000 0.0154 0.0577 0.322 + 65 0.3698 4.1268 0.6730 -0.8966 -0.0253 -0.2785 -0.2172 0.0046 0.0000 0.0140 0.0572 0.314 + 66 0.5474 4.0565 0.7936 -0.8963 -0.0253 -0.2833 -0.2209 0.0041 0.0000 0.0123 0.0566 0.306 + 67 0.7617 3.9717 0.9441 -0.8943 -0.0249 -0.2887 -0.2252 0.0037 0.0000 0.0105 0.0559 0.297 + 68 1.0116 3.8728 1.0344 -0.8910 -0.0240 -0.2950 -0.2301 0.0031 0.0000 0.0087 0.0554 0.288 + 69 1.2891 3.7630 1.1046 -0.8844 -0.0224 -0.3014 -0.2351 0.0026 0.0000 0.0070 0.0550 0.280 + 70 1.5912 3.6435 1.1542 -0.8745 -0.0203 -0.3078 -0.2401 0.0021 0.0000 0.0054 0.0547 0.273 + 71 1.9146 3.5155 1.1831 -0.8607 -0.0183 -0.3141 -0.2449 0.0017 0.0000 0.0040 0.0545 0.266 + 72 2.2558 3.3805 1.1921 -0.8435 -0.0167 -0.3201 -0.2496 0.0011 0.0000 0.0028 0.0545 0.261 + 73 2.6109 3.2400 1.1821 -0.8218 -0.0159 -0.3254 -0.2538 0.0008 0.0000 0.0017 0.0544 0.257 + 74 2.9762 3.0955 1.1548 -0.7958 -0.0159 -0.3298 -0.2572 0.0005 0.0000 0.0007 0.0543 0.253 + 75 3.3476 2.9485 1.1122 -0.7666 -0.0164 -0.3336 -0.2602 0.0001 0.0000 -0.0002 0.0541 0.249 + 76 3.7210 2.8008 1.0564 -0.7338 -0.0172 -0.3362 -0.2622 -0.0001 0.0000 -0.0011 0.0538 0.246 + 77 4.0924 2.6538 0.9900 -0.6979 -0.0182 -0.3374 -0.2631 -0.0003 0.0000 -0.0020 0.0533 0.242 + 78 4.4577 2.5093 0.9155 -0.6594 -0.0193 -0.3372 -0.2630 -0.0006 0.0000 -0.0030 0.0524 0.239 + 79 4.8128 2.3687 0.8353 -0.6189 -0.0204 -0.3353 -0.2615 -0.0008 0.0000 -0.0041 0.0511 0.234 + 80 5.1540 2.2338 0.7518 -0.5764 -0.0216 -0.3311 -0.2582 -0.0009 0.0000 -0.0055 0.0492 0.229 + 81 5.4774 2.1058 0.6671 -0.5323 -0.0228 -0.3244 -0.2530 -0.0012 0.0000 -0.0072 0.0467 0.222 + 82 5.7795 1.9862 0.5830 -0.4868 -0.0240 -0.3145 -0.2453 -0.0015 0.0000 -0.0091 0.0435 0.213 + 83 6.0570 1.8764 0.5012 -0.4395 -0.0251 -0.3006 -0.2344 -0.0018 0.0000 -0.0113 0.0393 0.202 + 84 6.3069 1.7776 0.4225 -0.3905 -0.0261 -0.2819 -0.2199 -0.0020 0.0000 -0.0135 0.0344 0.188 + 85 6.5264 1.6907 0.3478 -0.3400 -0.0270 -0.2581 -0.2013 -0.0024 0.0000 -0.0155 0.0289 0.173 + 86 6.7314 1.6096 0.3326 -0.2854 -0.0278 -0.2276 -0.1775 -0.0027 0.0000 -0.0168 0.0228 0.156 + 87 6.9144 1.5372 0.2507 -0.2246 -0.0285 -0.1876 -0.1463 -0.0029 0.0000 -0.0167 0.0164 0.136 + 88 7.0535 1.4822 0.1746 -0.1620 -0.0290 -0.1404 -0.1095 -0.0031 0.0000 -0.0146 0.0105 0.117 + 89 7.1471 1.4451 0.1029 -0.0978 -0.0294 -0.0869 -0.0678 -0.0028 0.0000 -0.0101 0.0056 0.101 + 90 7.1941 1.4265 0.0340 -0.0327 -0.0295 -0.0295 -0.0230 -0.0023 0.0000 -0.0036 0.0017 0.094 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.03886 Clsurf = -0.00383 - CYsurf = -0.00618 Cmsurf = 0.18693 - CDsurf = 0.00029 Cnsurf = 0.00382 - CDisurf = 0.00029 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.03913 Clsurf = -0.00386 + CYsurf = -0.00622 Cmsurf = 0.18821 + CDsurf = 0.00028 Cnsurf = 0.00385 + CDisurf = 0.00028 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.23684 CDsurf = 0.00174 + CLsurf = -0.23849 CDsurf = 0.00169 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.6657 -0.0234 -0.1937 -0.1511 0.1412 0.0000 0.0150 -0.0452 0.349 - 92 -0.0418 4.2566 0.2392 -0.8680 -0.0240 -0.2609 -0.2035 0.0161 0.0000 0.0165 -0.0566 0.331 - 93 -0.1156 4.2274 0.3930 -0.8842 -0.0246 -0.2680 -0.2090 0.0071 0.0000 0.0162 -0.0574 0.328 - 94 -0.2254 4.1839 0.5386 -0.8881 -0.0251 -0.2721 -0.2122 0.0053 0.0000 0.0153 -0.0573 0.322 - 95 -0.3698 4.1268 0.6730 -0.8901 -0.0254 -0.2765 -0.2157 0.0046 0.0000 0.0139 -0.0568 0.314 - 96 -0.5474 4.0565 0.7936 -0.8896 -0.0254 -0.2812 -0.2193 0.0042 0.0000 0.0122 -0.0562 0.306 - 97 -0.7617 3.9717 0.9441 -0.8875 -0.0251 -0.2865 -0.2235 0.0037 0.0000 0.0105 -0.0555 0.297 - 98 -1.0116 3.8728 1.0344 -0.8839 -0.0241 -0.2927 -0.2283 0.0031 0.0000 0.0087 -0.0550 0.288 - 99 -1.2891 3.7630 1.1046 -0.8774 -0.0225 -0.2990 -0.2332 0.0026 0.0000 0.0070 -0.0546 0.280 - 100 -1.5912 3.6435 1.1542 -0.8672 -0.0205 -0.3053 -0.2381 0.0021 0.0000 0.0054 -0.0543 0.273 - 101 -1.9146 3.5155 1.1831 -0.8542 -0.0184 -0.3117 -0.2431 0.0017 0.0000 0.0040 -0.0541 0.266 - 102 -2.2558 3.3805 1.1921 -0.8370 -0.0168 -0.3176 -0.2477 0.0012 0.0000 0.0028 -0.0541 0.261 - 103 -2.6109 3.2400 1.1821 -0.8156 -0.0160 -0.3229 -0.2518 0.0009 0.0000 0.0017 -0.0540 0.257 - 104 -2.9762 3.0955 1.1548 -0.7901 -0.0160 -0.3275 -0.2554 0.0005 0.0000 0.0007 -0.0539 0.253 - 105 -3.3476 2.9485 1.1122 -0.7611 -0.0165 -0.3312 -0.2583 0.0002 0.0000 -0.0002 -0.0538 0.249 - 106 -3.7210 2.8008 1.0564 -0.7285 -0.0173 -0.3337 -0.2603 -0.0000 0.0000 -0.0010 -0.0534 0.246 - 107 -4.0924 2.6538 0.9900 -0.6931 -0.0183 -0.3351 -0.2613 -0.0003 0.0000 -0.0019 -0.0529 0.243 - 108 -4.4577 2.5093 0.9155 -0.6551 -0.0194 -0.3350 -0.2612 -0.0005 0.0000 -0.0029 -0.0521 0.239 - 109 -4.8128 2.3687 0.8353 -0.6154 -0.0205 -0.3333 -0.2600 -0.0007 0.0000 -0.0041 -0.0508 0.234 - 110 -5.1540 2.2338 0.7518 -0.5733 -0.0217 -0.3293 -0.2568 -0.0009 0.0000 -0.0055 -0.0490 0.229 - 111 -5.4774 2.1058 0.6671 -0.5296 -0.0228 -0.3227 -0.2517 -0.0011 0.0000 -0.0071 -0.0465 0.222 - 112 -5.7795 1.9862 0.5830 -0.4842 -0.0240 -0.3128 -0.2440 -0.0014 0.0000 -0.0091 -0.0432 0.213 - 113 -6.0570 1.8764 0.5012 -0.4374 -0.0251 -0.2992 -0.2333 -0.0017 0.0000 -0.0113 -0.0391 0.202 - 114 -6.3069 1.7776 0.4225 -0.3888 -0.0261 -0.2807 -0.2189 -0.0020 0.0000 -0.0135 -0.0343 0.188 - 115 -6.5264 1.6907 0.3478 -0.3386 -0.0270 -0.2571 -0.2005 -0.0024 0.0000 -0.0154 -0.0288 0.173 - 116 -6.7314 1.6096 0.3326 -0.2843 -0.0278 -0.2267 -0.1768 -0.0026 0.0000 -0.0167 -0.0227 0.155 - 117 -6.9144 1.5372 0.2507 -0.2238 -0.0285 -0.1870 -0.1458 -0.0029 0.0000 -0.0167 -0.0163 0.136 - 118 -7.0535 1.4822 0.1746 -0.1614 -0.0290 -0.1398 -0.1090 -0.0030 0.0000 -0.0145 -0.0104 0.117 - 119 -7.1471 1.4451 0.1029 -0.0974 -0.0294 -0.0866 -0.0676 -0.0027 0.0000 -0.0101 -0.0056 0.101 - 120 -7.1941 1.4265 0.0340 -0.0326 -0.0295 -0.0294 -0.0229 -0.0023 0.0000 -0.0036 -0.0017 0.094 + 91 -0.0047 4.2713 0.0803 -0.6689 -0.0232 -0.1946 -0.1518 0.1434 0.0000 0.0151 -0.0454 0.349 + 92 -0.0418 4.2566 0.2392 -0.8746 -0.0238 -0.2629 -0.2050 0.0163 0.0000 0.0166 -0.0570 0.331 + 93 -0.1156 4.2274 0.3930 -0.8912 -0.0245 -0.2702 -0.2107 0.0071 0.0000 0.0163 -0.0578 0.327 + 94 -0.2254 4.1839 0.5386 -0.8950 -0.0250 -0.2742 -0.2139 0.0052 0.0000 0.0154 -0.0577 0.322 + 95 -0.3698 4.1268 0.6730 -0.8966 -0.0253 -0.2785 -0.2172 0.0046 0.0000 0.0140 -0.0572 0.314 + 96 -0.5474 4.0565 0.7936 -0.8963 -0.0253 -0.2833 -0.2209 0.0041 0.0000 0.0123 -0.0566 0.306 + 97 -0.7617 3.9717 0.9441 -0.8943 -0.0249 -0.2887 -0.2252 0.0037 0.0000 0.0105 -0.0559 0.297 + 98 -1.0116 3.8728 1.0344 -0.8910 -0.0240 -0.2950 -0.2301 0.0031 0.0000 0.0087 -0.0554 0.288 + 99 -1.2891 3.7630 1.1046 -0.8844 -0.0224 -0.3014 -0.2351 0.0026 0.0000 0.0070 -0.0550 0.280 + 100 -1.5912 3.6435 1.1542 -0.8745 -0.0203 -0.3078 -0.2401 0.0021 0.0000 0.0054 -0.0547 0.273 + 101 -1.9146 3.5155 1.1831 -0.8607 -0.0183 -0.3141 -0.2449 0.0017 0.0000 0.0040 -0.0545 0.266 + 102 -2.2558 3.3805 1.1921 -0.8435 -0.0167 -0.3201 -0.2496 0.0011 0.0000 0.0028 -0.0545 0.261 + 103 -2.6109 3.2400 1.1821 -0.8218 -0.0159 -0.3254 -0.2538 0.0008 0.0000 0.0017 -0.0544 0.257 + 104 -2.9762 3.0955 1.1548 -0.7958 -0.0159 -0.3298 -0.2572 0.0005 0.0000 0.0007 -0.0543 0.253 + 105 -3.3476 2.9485 1.1122 -0.7666 -0.0164 -0.3336 -0.2602 0.0001 0.0000 -0.0002 -0.0541 0.249 + 106 -3.7210 2.8008 1.0564 -0.7338 -0.0172 -0.3362 -0.2622 -0.0001 0.0000 -0.0011 -0.0538 0.246 + 107 -4.0924 2.6538 0.9900 -0.6979 -0.0182 -0.3374 -0.2631 -0.0003 0.0000 -0.0020 -0.0533 0.242 + 108 -4.4577 2.5093 0.9155 -0.6594 -0.0193 -0.3372 -0.2630 -0.0006 0.0000 -0.0030 -0.0524 0.239 + 109 -4.8128 2.3687 0.8353 -0.6189 -0.0204 -0.3353 -0.2615 -0.0008 0.0000 -0.0041 -0.0511 0.234 + 110 -5.1540 2.2338 0.7518 -0.5764 -0.0216 -0.3311 -0.2582 -0.0009 0.0000 -0.0055 -0.0492 0.229 + 111 -5.4774 2.1058 0.6671 -0.5323 -0.0228 -0.3244 -0.2530 -0.0012 0.0000 -0.0072 -0.0467 0.222 + 112 -5.7795 1.9862 0.5830 -0.4868 -0.0240 -0.3145 -0.2453 -0.0015 0.0000 -0.0091 -0.0435 0.213 + 113 -6.0570 1.8764 0.5012 -0.4395 -0.0251 -0.3006 -0.2344 -0.0018 0.0000 -0.0113 -0.0393 0.202 + 114 -6.3069 1.7776 0.4225 -0.3905 -0.0261 -0.2819 -0.2199 -0.0020 0.0000 -0.0135 -0.0344 0.188 + 115 -6.5264 1.6907 0.3478 -0.3400 -0.0270 -0.2581 -0.2013 -0.0024 0.0000 -0.0155 -0.0289 0.173 + 116 -6.7314 1.6096 0.3326 -0.2854 -0.0278 -0.2276 -0.1775 -0.0027 0.0000 -0.0168 -0.0228 0.156 + 117 -6.9144 1.5372 0.2507 -0.2246 -0.0285 -0.1876 -0.1463 -0.0029 0.0000 -0.0167 -0.0164 0.136 + 118 -7.0535 1.4822 0.1746 -0.1620 -0.0290 -0.1404 -0.1095 -0.0031 0.0000 -0.0146 -0.0105 0.117 + 119 -7.1471 1.4451 0.1029 -0.0978 -0.0294 -0.0869 -0.0678 -0.0028 0.0000 -0.0101 -0.0056 0.101 + 120 -7.1941 1.4265 0.0340 -0.0327 -0.0295 -0.0295 -0.0230 -0.0023 0.0000 -0.0036 -0.0017 0.094 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = -0.00000 Clsurf = -0.00000 CYsurf = -0.00000 Cmsurf = 0.00000 CDsurf = 0.00000 Cnsurf = 0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.776 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.774 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.764 - 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.756 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.742 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.723 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.697 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.662 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.616 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.554 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.503 + 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.769 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.769 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.763 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.753 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.740 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.719 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.694 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.659 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.615 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.553 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.502 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.474 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.448 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.449 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.422 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.396 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.373 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.351 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.332 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.313 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.300 - 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.285 - 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.270 + 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.399 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.374 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.350 + 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.331 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.317 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.299 + 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.283 + 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.269 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.253 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.235 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.216 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.193 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.171 - 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.149 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.134 - 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.125 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.192 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.173 + 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.151 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.135 + 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.127 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00957 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.02665 - CDsurf = 0.00021 Cnsurf = 0.00000 - CDisurf = 0.00021 CDvsurf = 0.00000 + CLsurf = -0.00964 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.02659 + CDsurf = 0.00022 Cnsurf = 0.00000 + CDisurf = 0.00022 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00965 CDsurf = 0.00022 + CLsurf = -0.00972 CDsurf = 0.00022 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.2484 -0.0654 -0.1162 -0.0093 0.0000 0.0000 -0.0004 0.0003 0.206 - 152 -1.3090 31.2096 11.6724 -0.3333 -0.0643 -0.0415 -0.0107 0.0002 0.0000 -0.0009 0.0004 0.165 - 153 -0.9350 34.0626 12.7394 -0.3406 -0.0326 -0.0244 -0.0100 0.0002 0.0000 -0.0020 0.0002 0.051 - 154 -0.5610 36.1619 13.5246 -0.3384 -0.0194 -0.0157 -0.0094 0.0003 0.0000 -0.0026 -0.0001 -0.027 - 155 -0.1870 37.5332 14.0374 -0.3370 -0.0153 -0.0104 -0.0090 0.0003 0.0000 -0.0028 -0.0004 -0.065 - 156 0.1870 37.5332 14.0374 -0.3370 -0.0153 -0.0104 -0.0090 0.0003 0.0000 -0.0028 -0.0004 -0.065 - 157 0.5610 36.1619 13.5246 -0.3384 -0.0194 -0.0157 -0.0094 0.0003 0.0000 -0.0026 -0.0001 -0.027 - 158 0.9350 34.0626 12.7394 -0.3406 -0.0326 -0.0244 -0.0100 0.0002 0.0000 -0.0020 0.0002 0.051 - 159 1.3090 31.2096 11.6724 -0.3333 -0.0643 -0.0415 -0.0107 0.0002 0.0000 -0.0009 0.0004 0.165 - 160 1.6830 26.5957 9.9468 -0.2484 -0.0654 -0.1162 -0.0093 0.0000 0.0000 -0.0004 0.0003 0.206 + 151 -1.6830 26.5957 9.9468 -0.2504 -0.0655 -0.1171 -0.0094 0.0000 0.0000 -0.0004 0.0003 0.209 + 152 -1.3090 31.2096 11.6724 -0.3359 -0.0644 -0.0418 -0.0108 0.0002 0.0000 -0.0009 0.0005 0.169 + 153 -0.9350 34.0626 12.7394 -0.3431 -0.0325 -0.0246 -0.0101 0.0002 0.0000 -0.0020 0.0002 0.055 + 154 -0.5610 36.1619 13.5246 -0.3407 -0.0192 -0.0158 -0.0094 0.0003 0.0000 -0.0026 -0.0001 -0.024 + 155 -0.1870 37.5332 14.0374 -0.3393 -0.0152 -0.0105 -0.0090 0.0003 0.0000 -0.0028 -0.0004 -0.062 + 156 0.1870 37.5332 14.0374 -0.3393 -0.0152 -0.0105 -0.0090 0.0003 0.0000 -0.0028 -0.0004 -0.062 + 157 0.5610 36.1619 13.5246 -0.3407 -0.0192 -0.0158 -0.0094 0.0003 0.0000 -0.0026 -0.0001 -0.024 + 158 0.9350 34.0626 12.7394 -0.3431 -0.0325 -0.0246 -0.0101 0.0002 0.0000 -0.0020 0.0002 0.055 + 159 1.3090 31.2096 11.6724 -0.3359 -0.0644 -0.0418 -0.0108 0.0002 0.0000 -0.0009 0.0005 0.169 + 160 1.6830 26.5957 9.9468 -0.2504 -0.0655 -0.1171 -0.0094 0.0000 0.0000 -0.0004 0.0003 0.209 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.993 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.908 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0002 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.899 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.890 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.886 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.871 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.857 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.830 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.686 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.363 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.077 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.931 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.911 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.902 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.898 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.885 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.868 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.841 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.682 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.344 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_06_02.txt b/regression/scripts/AVL/avl_files/strip_forces_case_06_02.txt index 12c9bbcf9e..7235f9cd8c 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_06_02.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_06_02.txt @@ -7,188 +7,188 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.13163 Clsurf = -0.02281 - CYsurf = -0.00945 Cmsurf = -0.11546 - CDsurf = 0.00204 Cnsurf = 0.00104 - CDisurf = 0.00204 CDvsurf = 0.00000 + CLsurf = 0.13260 Clsurf = -0.02291 + CYsurf = -0.00950 Cmsurf = -0.11598 + CDsurf = 0.00207 Cnsurf = 0.00105 + CDisurf = 0.00207 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25759 CDsurf = 0.00398 + CLsurf = 0.25949 CDsurf = 0.00404 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 2.0712 0.0529 0.3445 0.2672 0.1546 0.0000 -0.0223 -0.0726 0.333 - 2 0.1025 7.6885 1.0492 1.9599 0.0521 0.3287 0.2549 0.0279 0.0000 -0.0219 -0.0698 0.336 - 3 0.2837 7.5620 1.7073 1.9473 0.0505 0.3320 0.2575 0.0193 0.0000 -0.0213 -0.0698 0.333 - 4 0.5530 7.3741 2.3052 1.9337 0.0478 0.3381 0.2622 0.0170 0.0000 -0.0201 -0.0698 0.327 - 5 0.9075 7.1267 2.8223 1.9087 0.0442 0.3453 0.2678 0.0153 0.0000 -0.0187 -0.0698 0.320 - 6 1.3432 6.8226 3.2414 1.8665 0.0414 0.3527 0.2736 0.0126 0.0000 -0.0176 -0.0701 0.314 - 7 1.8554 6.4651 3.5491 1.8041 0.0433 0.3598 0.2791 0.0105 0.0000 -0.0169 -0.0706 0.311 - 8 2.4386 6.0582 3.7368 1.7168 0.0438 0.3654 0.2834 0.0084 0.0000 -0.0169 -0.0715 0.310 - 9 3.0862 5.6062 3.8005 1.6035 0.0351 0.3688 0.2860 0.0048 0.0000 -0.0180 -0.0729 0.313 - 10 3.7613 5.1351 3.4440 1.4772 0.0250 0.3709 0.2877 0.0031 0.0000 -0.0202 -0.0750 0.320 - 11 4.4532 4.6522 3.3149 1.3392 0.0154 0.3711 0.2879 -0.0000 0.0000 -0.0238 -0.0781 0.333 - 12 5.1831 4.1429 3.0930 1.1929 0.0025 0.3712 0.2879 -0.0029 0.0000 -0.0288 -0.0821 0.350 - 13 6.0123 3.7903 3.4706 1.0574 -0.0050 0.3398 0.2790 -0.0040 0.0000 -0.0319 -0.0903 0.364 - 14 6.9353 3.6075 3.3775 0.9571 -0.0011 0.3231 0.2653 -0.0031 0.0000 -0.0324 -0.0878 0.372 - 15 7.8737 3.4215 3.2389 0.8731 0.0015 0.3108 0.2552 -0.0026 0.0000 -0.0325 -0.0856 0.377 - 16 8.8172 3.2345 3.0619 0.8000 0.0031 0.3012 0.2473 -0.0023 0.0000 -0.0324 -0.0837 0.381 - 17 9.7556 3.0486 2.8543 0.7348 0.0039 0.2935 0.2410 -0.0021 0.0000 -0.0322 -0.0822 0.384 - 18 10.6786 2.8657 2.6240 0.6759 0.0043 0.2873 0.2359 -0.0020 0.0000 -0.0321 -0.0809 0.386 - 19 11.5760 2.6879 2.3787 0.6219 0.0046 0.2818 0.2314 -0.0019 0.0000 -0.0318 -0.0797 0.388 - 20 12.4328 2.5181 2.1010 0.5719 0.0051 0.2766 0.2271 -0.0018 0.0000 -0.0315 -0.0784 0.389 - 21 13.2400 2.3582 1.8520 0.5250 0.0059 0.2711 0.2226 -0.0017 0.0000 -0.0309 -0.0770 0.389 - 22 13.9941 2.2087 1.6074 0.4795 0.0070 0.2644 0.2171 -0.0017 0.0000 -0.0301 -0.0750 0.389 - 23 14.6868 2.0715 1.3716 0.4341 0.0086 0.2552 0.2096 -0.0016 0.0000 -0.0288 -0.0721 0.387 - 24 15.3105 1.9479 1.1479 0.3870 0.0104 0.2420 0.1987 -0.0015 0.0000 -0.0269 -0.0680 0.385 - 25 15.8583 1.8393 0.9381 0.3364 0.0125 0.2228 0.1829 -0.0014 0.0000 -0.0246 -0.0625 0.384 - 26 16.3244 1.7470 0.7427 0.2811 0.0150 0.1960 0.1609 -0.0013 0.0000 -0.0225 -0.0557 0.390 - 27 16.6722 1.4928 0.4131 0.2229 0.0175 0.4984 0.1493 -0.0022 0.0000 -0.0176 -0.0257 0.368 - 28 16.9098 1.1466 0.2292 0.1645 0.0213 0.4788 0.1434 -0.0036 0.0000 -0.0090 -0.0210 0.312 - 29 17.0696 0.9138 0.1104 0.1013 0.0241 0.3700 0.1108 -0.0047 0.0000 0.0002 -0.0129 0.248 - 30 17.1499 0.7967 0.0322 0.0342 0.0253 0.1433 0.0429 -0.0030 0.0000 0.0021 -0.0041 0.202 + 1 0.0114 7.7520 0.3539 2.0953 0.0523 0.3485 0.2703 0.1559 0.0000 -0.0243 -0.0748 0.340 + 2 0.1025 7.6885 1.0491 1.9798 0.0516 0.3320 0.2575 0.0280 0.0000 -0.0235 -0.0716 0.341 + 3 0.2837 7.5620 1.7073 1.9671 0.0503 0.3354 0.2601 0.0192 0.0000 -0.0229 -0.0716 0.338 + 4 0.5530 7.3741 2.3052 1.9538 0.0480 0.3416 0.2650 0.0167 0.0000 -0.0217 -0.0717 0.332 + 5 0.9075 7.1267 2.8223 1.9297 0.0447 0.3491 0.2708 0.0151 0.0000 -0.0205 -0.0718 0.326 + 6 1.3432 6.8226 3.2414 1.8889 0.0421 0.3569 0.2769 0.0135 0.0000 -0.0193 -0.0722 0.320 + 7 1.8554 6.4651 3.5491 1.8260 0.0441 0.3641 0.2824 0.0109 0.0000 -0.0186 -0.0727 0.316 + 8 2.4386 6.0582 3.7368 1.7383 0.0448 0.3699 0.2869 0.0084 0.0000 -0.0186 -0.0736 0.315 + 9 3.0862 5.6062 3.8005 1.6258 0.0369 0.3739 0.2900 0.0054 0.0000 -0.0196 -0.0751 0.318 + 10 3.7613 5.1351 3.4440 1.4996 0.0265 0.3765 0.2920 0.0025 0.0000 -0.0212 -0.0767 0.323 + 11 4.4532 4.6522 3.3149 1.3504 0.0154 0.3743 0.2903 0.0003 0.0000 -0.0236 -0.0784 0.331 + 12 5.1831 4.1429 3.0930 1.1991 0.0012 0.3732 0.2894 -0.0030 0.0000 -0.0274 -0.0813 0.345 + 13 6.0123 3.7903 3.4706 1.0624 -0.0056 0.3414 0.2803 -0.0040 0.0000 -0.0299 -0.0888 0.357 + 14 6.9353 3.6075 3.3775 0.9611 -0.0015 0.3245 0.2664 -0.0031 0.0000 -0.0301 -0.0859 0.363 + 15 7.8737 3.4215 3.2389 0.8764 0.0013 0.3120 0.2561 -0.0026 0.0000 -0.0300 -0.0836 0.367 + 16 8.8172 3.2345 3.0619 0.8027 0.0029 0.3022 0.2482 -0.0024 0.0000 -0.0298 -0.0816 0.370 + 17 9.7556 3.0486 2.8543 0.7371 0.0037 0.2945 0.2418 -0.0021 0.0000 -0.0296 -0.0800 0.373 + 18 10.6786 2.8657 2.6239 0.6778 0.0042 0.2881 0.2365 -0.0020 0.0000 -0.0294 -0.0787 0.374 + 19 11.5760 2.6879 2.3787 0.6235 0.0045 0.2825 0.2320 -0.0019 0.0000 -0.0292 -0.0775 0.376 + 20 12.4328 2.5181 2.1010 0.5732 0.0051 0.2772 0.2276 -0.0018 0.0000 -0.0288 -0.0762 0.377 + 21 13.2400 2.3582 1.8520 0.5259 0.0059 0.2716 0.2230 -0.0017 0.0000 -0.0282 -0.0747 0.377 + 22 13.9941 2.2087 1.6074 0.4802 0.0070 0.2648 0.2174 -0.0017 0.0000 -0.0274 -0.0726 0.376 + 23 14.6868 2.0715 1.3716 0.4344 0.0085 0.2554 0.2097 -0.0016 0.0000 -0.0261 -0.0698 0.374 + 24 15.3105 1.9479 1.1479 0.3869 0.0104 0.2419 0.1986 -0.0016 0.0000 -0.0242 -0.0656 0.372 + 25 15.8583 1.8393 0.9381 0.3359 0.0124 0.2224 0.1826 -0.0014 0.0000 -0.0219 -0.0600 0.370 + 26 16.3244 1.7470 0.7427 0.2797 0.0144 0.1950 0.1601 -0.0013 0.0000 -0.0198 -0.0531 0.373 + 27 16.6722 1.4928 0.4131 0.2217 0.0169 0.4957 0.1485 -0.0023 0.0000 -0.0154 -0.0246 0.354 + 28 16.9098 1.1466 0.2292 0.1637 0.0210 0.4765 0.1428 -0.0037 0.0000 -0.0071 -0.0200 0.300 + 29 17.0696 0.9138 0.1104 0.1009 0.0239 0.3685 0.1104 -0.0048 0.0000 0.0014 -0.0122 0.237 + 30 17.1499 0.7967 0.0322 0.0342 0.0261 0.1431 0.0429 -0.0031 0.0000 0.0025 -0.0039 0.193 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.13163 Clsurf = 0.02281 - CYsurf = 0.00945 Cmsurf = -0.11546 - CDsurf = 0.00204 Cnsurf = -0.00104 - CDisurf = 0.00204 CDvsurf = 0.00000 + CLsurf = 0.13260 Clsurf = 0.02291 + CYsurf = 0.00950 Cmsurf = -0.11598 + CDsurf = 0.00207 Cnsurf = -0.00105 + CDisurf = 0.00207 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.25759 CDsurf = 0.00398 + CLsurf = 0.25949 CDsurf = 0.00404 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 2.0711 0.0528 0.3445 0.2672 0.1546 0.0000 -0.0223 0.0726 0.333 - 32 -0.1025 7.6885 1.0492 1.9599 0.0521 0.3287 0.2549 0.0279 0.0000 -0.0219 0.0698 0.336 - 33 -0.2837 7.5620 1.7073 1.9473 0.0505 0.3320 0.2575 0.0193 0.0000 -0.0213 0.0698 0.333 - 34 -0.5530 7.3741 2.3052 1.9337 0.0478 0.3381 0.2622 0.0170 0.0000 -0.0201 0.0698 0.327 - 35 -0.9075 7.1267 2.8223 1.9087 0.0442 0.3453 0.2678 0.0153 0.0000 -0.0187 0.0698 0.320 - 36 -1.3432 6.8226 3.2414 1.8664 0.0414 0.3527 0.2736 0.0126 0.0000 -0.0176 0.0701 0.314 - 37 -1.8554 6.4651 3.5491 1.8041 0.0433 0.3598 0.2791 0.0105 0.0000 -0.0169 0.0706 0.311 - 38 -2.4386 6.0582 3.7368 1.7168 0.0438 0.3654 0.2834 0.0084 0.0000 -0.0169 0.0715 0.310 - 39 -3.0862 5.6062 3.8005 1.6035 0.0351 0.3688 0.2860 0.0048 0.0000 -0.0180 0.0729 0.313 - 40 -3.7613 5.1351 3.4440 1.4772 0.0250 0.3709 0.2877 0.0031 0.0000 -0.0202 0.0750 0.320 - 41 -4.4532 4.6522 3.3149 1.3391 0.0154 0.3711 0.2878 -0.0000 0.0000 -0.0238 0.0781 0.333 - 42 -5.1831 4.1429 3.0930 1.1929 0.0025 0.3712 0.2879 -0.0029 0.0000 -0.0288 0.0821 0.350 - 43 -6.0123 3.7903 3.4706 1.0574 -0.0050 0.3398 0.2790 -0.0040 0.0000 -0.0319 0.0903 0.364 - 44 -6.9353 3.6075 3.3775 0.9571 -0.0011 0.3231 0.2653 -0.0031 0.0000 -0.0324 0.0878 0.372 - 45 -7.8737 3.4215 3.2389 0.8731 0.0015 0.3108 0.2552 -0.0026 0.0000 -0.0325 0.0856 0.377 - 46 -8.8172 3.2345 3.0619 0.8000 0.0031 0.3012 0.2473 -0.0023 0.0000 -0.0324 0.0837 0.381 - 47 -9.7556 3.0486 2.8543 0.7348 0.0039 0.2935 0.2410 -0.0021 0.0000 -0.0322 0.0822 0.384 - 48 -10.6786 2.8657 2.6240 0.6759 0.0043 0.2872 0.2359 -0.0020 0.0000 -0.0321 0.0809 0.386 - 49 -11.5760 2.6879 2.3787 0.6219 0.0046 0.2818 0.2314 -0.0019 0.0000 -0.0318 0.0797 0.388 - 50 -12.4328 2.5181 2.1010 0.5719 0.0051 0.2766 0.2271 -0.0018 0.0000 -0.0315 0.0784 0.389 - 51 -13.2400 2.3582 1.8520 0.5250 0.0059 0.2711 0.2226 -0.0017 0.0000 -0.0309 0.0770 0.389 - 52 -13.9941 2.2087 1.6074 0.4795 0.0070 0.2644 0.2171 -0.0017 0.0000 -0.0301 0.0750 0.389 - 53 -14.6868 2.0715 1.3716 0.4341 0.0086 0.2552 0.2096 -0.0016 0.0000 -0.0288 0.0721 0.387 - 54 -15.3105 1.9479 1.1479 0.3870 0.0104 0.2420 0.1987 -0.0015 0.0000 -0.0269 0.0680 0.385 - 55 -15.8583 1.8393 0.9381 0.3364 0.0125 0.2228 0.1829 -0.0014 0.0000 -0.0246 0.0625 0.384 - 56 -16.3244 1.7470 0.7427 0.2811 0.0150 0.1960 0.1609 -0.0013 0.0000 -0.0225 0.0557 0.390 - 57 -16.6722 1.4928 0.4131 0.2229 0.0175 0.4984 0.1493 -0.0022 0.0000 -0.0176 0.0257 0.368 - 58 -16.9098 1.1466 0.2292 0.1645 0.0213 0.4788 0.1434 -0.0036 0.0000 -0.0090 0.0210 0.312 - 59 -17.0696 0.9138 0.1104 0.1013 0.0241 0.3700 0.1108 -0.0047 0.0000 0.0002 0.0129 0.248 - 60 -17.1499 0.7967 0.0322 0.0342 0.0253 0.1433 0.0429 -0.0030 0.0000 0.0021 0.0041 0.202 + 31 -0.0114 7.7520 0.3539 2.0953 0.0523 0.3485 0.2703 0.1559 0.0000 -0.0243 0.0748 0.340 + 32 -0.1025 7.6885 1.0491 1.9798 0.0516 0.3320 0.2575 0.0280 0.0000 -0.0235 0.0716 0.341 + 33 -0.2837 7.5620 1.7073 1.9671 0.0503 0.3354 0.2601 0.0192 0.0000 -0.0229 0.0716 0.338 + 34 -0.5530 7.3741 2.3052 1.9538 0.0480 0.3416 0.2650 0.0167 0.0000 -0.0217 0.0717 0.332 + 35 -0.9075 7.1267 2.8223 1.9297 0.0447 0.3491 0.2708 0.0151 0.0000 -0.0205 0.0718 0.326 + 36 -1.3432 6.8226 3.2414 1.8889 0.0421 0.3569 0.2769 0.0135 0.0000 -0.0193 0.0722 0.320 + 37 -1.8554 6.4651 3.5491 1.8260 0.0441 0.3641 0.2824 0.0109 0.0000 -0.0186 0.0727 0.316 + 38 -2.4386 6.0582 3.7368 1.7383 0.0448 0.3699 0.2869 0.0084 0.0000 -0.0186 0.0736 0.315 + 39 -3.0862 5.6062 3.8005 1.6258 0.0369 0.3739 0.2900 0.0054 0.0000 -0.0196 0.0751 0.318 + 40 -3.7613 5.1351 3.4440 1.4996 0.0265 0.3765 0.2920 0.0025 0.0000 -0.0212 0.0767 0.323 + 41 -4.4532 4.6522 3.3149 1.3504 0.0154 0.3743 0.2903 0.0003 0.0000 -0.0236 0.0784 0.331 + 42 -5.1831 4.1429 3.0930 1.1991 0.0012 0.3732 0.2894 -0.0030 0.0000 -0.0274 0.0813 0.345 + 43 -6.0123 3.7903 3.4706 1.0624 -0.0056 0.3414 0.2803 -0.0040 0.0000 -0.0299 0.0888 0.357 + 44 -6.9353 3.6075 3.3775 0.9611 -0.0015 0.3245 0.2664 -0.0031 0.0000 -0.0301 0.0859 0.363 + 45 -7.8737 3.4215 3.2389 0.8764 0.0013 0.3120 0.2561 -0.0026 0.0000 -0.0300 0.0836 0.367 + 46 -8.8172 3.2345 3.0619 0.8027 0.0029 0.3022 0.2482 -0.0024 0.0000 -0.0298 0.0816 0.370 + 47 -9.7556 3.0486 2.8543 0.7371 0.0037 0.2945 0.2418 -0.0021 0.0000 -0.0296 0.0800 0.373 + 48 -10.6786 2.8657 2.6239 0.6778 0.0042 0.2881 0.2365 -0.0020 0.0000 -0.0294 0.0787 0.374 + 49 -11.5760 2.6879 2.3787 0.6235 0.0045 0.2825 0.2320 -0.0019 0.0000 -0.0292 0.0775 0.376 + 50 -12.4328 2.5181 2.1010 0.5732 0.0051 0.2772 0.2276 -0.0018 0.0000 -0.0288 0.0762 0.377 + 51 -13.2400 2.3582 1.8520 0.5259 0.0059 0.2716 0.2230 -0.0017 0.0000 -0.0282 0.0747 0.377 + 52 -13.9941 2.2087 1.6074 0.4802 0.0070 0.2648 0.2174 -0.0017 0.0000 -0.0274 0.0726 0.376 + 53 -14.6868 2.0715 1.3716 0.4344 0.0085 0.2554 0.2097 -0.0016 0.0000 -0.0261 0.0698 0.374 + 54 -15.3105 1.9479 1.1479 0.3869 0.0104 0.2419 0.1986 -0.0016 0.0000 -0.0242 0.0656 0.372 + 55 -15.8583 1.8393 0.9381 0.3359 0.0124 0.2224 0.1826 -0.0014 0.0000 -0.0219 0.0600 0.370 + 56 -16.3244 1.7470 0.7427 0.2797 0.0144 0.1950 0.1601 -0.0013 0.0000 -0.0198 0.0531 0.373 + 57 -16.6722 1.4928 0.4131 0.2217 0.0169 0.4957 0.1485 -0.0023 0.0000 -0.0154 0.0246 0.354 + 58 -16.9098 1.1466 0.2292 0.1637 0.0210 0.4765 0.1428 -0.0037 0.0000 -0.0071 0.0200 0.300 + 59 -17.0696 0.9138 0.1104 0.1009 0.0239 0.3685 0.1104 -0.0048 0.0000 0.0014 0.0122 0.237 + 60 -17.1499 0.7967 0.0322 0.0342 0.0261 0.1431 0.0429 -0.0031 0.0000 0.0025 0.0039 0.193 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02033 Clsurf = 0.00193 - CYsurf = 0.00327 Cmsurf = 0.09762 - CDsurf = -0.00029 Cnsurf = -0.00197 - CDisurf = -0.00029 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02059 Clsurf = 0.00195 + CYsurf = 0.00332 Cmsurf = 0.09888 + CDsurf = -0.00030 Cnsurf = -0.00200 + CDisurf = -0.00030 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.12393 CDsurf = -0.00175 + CLsurf = -0.12555 CDsurf = -0.00180 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.4234 0.0133 -0.1279 -0.0991 0.0417 0.0000 0.0081 0.0277 0.332 - 62 0.0418 4.2566 0.2392 -0.4854 0.0129 -0.1471 -0.1140 0.0028 0.0000 0.0084 0.0312 0.324 - 63 0.1156 4.2274 0.3930 -0.4904 0.0124 -0.1496 -0.1160 -0.0001 0.0000 0.0082 0.0314 0.321 - 64 0.2254 4.1839 0.5386 -0.4916 0.0119 -0.1516 -0.1175 -0.0007 0.0000 0.0077 0.0313 0.315 - 65 0.3698 4.1268 0.6730 -0.4921 0.0114 -0.1538 -0.1192 -0.0009 0.0000 0.0069 0.0310 0.308 - 66 0.5474 4.0565 0.7936 -0.4915 0.0108 -0.1563 -0.1212 -0.0011 0.0000 0.0059 0.0306 0.299 - 67 0.7617 3.9717 0.9441 -0.4901 0.0104 -0.1592 -0.1234 -0.0013 0.0000 0.0049 0.0302 0.290 - 68 1.0116 3.8728 1.0344 -0.4875 0.0101 -0.1624 -0.1259 -0.0015 0.0000 0.0039 0.0298 0.281 - 69 1.2891 3.7630 1.1046 -0.4831 0.0100 -0.1656 -0.1284 -0.0017 0.0000 0.0029 0.0295 0.272 - 70 1.5912 3.6435 1.1542 -0.4764 0.0101 -0.1687 -0.1308 -0.0019 0.0000 0.0020 0.0293 0.265 - 71 1.9146 3.5155 1.1831 -0.4674 0.0103 -0.1715 -0.1329 -0.0021 0.0000 0.0012 0.0290 0.259 - 72 2.2558 3.3805 1.1921 -0.4555 0.0102 -0.1738 -0.1347 -0.0023 0.0000 0.0004 0.0288 0.253 - 73 2.6109 3.2400 1.1821 -0.4406 0.0098 -0.1754 -0.1360 -0.0024 0.0000 -0.0002 0.0285 0.249 - 74 2.9762 3.0955 1.1548 -0.4228 0.0091 -0.1762 -0.1366 -0.0025 0.0000 -0.0007 0.0282 0.245 - 75 3.3476 2.9485 1.1122 -0.4025 0.0082 -0.1761 -0.1365 -0.0026 0.0000 -0.0011 0.0278 0.242 - 76 3.7210 2.8008 1.0564 -0.3800 0.0073 -0.1750 -0.1357 -0.0026 0.0000 -0.0015 0.0273 0.239 - 77 4.0924 2.6538 0.9900 -0.3558 0.0064 -0.1729 -0.1341 -0.0026 0.0000 -0.0019 0.0267 0.236 - 78 4.4577 2.5093 0.9155 -0.3304 0.0056 -0.1699 -0.1317 -0.0025 0.0000 -0.0023 0.0259 0.233 - 79 4.8128 2.3687 0.8353 -0.3045 0.0048 -0.1658 -0.1286 -0.0024 0.0000 -0.0027 0.0249 0.229 - 80 5.1540 2.2338 0.7518 -0.2782 0.0041 -0.1606 -0.1245 -0.0024 0.0000 -0.0032 0.0236 0.224 - 81 5.4774 2.1058 0.6671 -0.2520 0.0035 -0.1543 -0.1196 -0.0023 0.0000 -0.0038 0.0221 0.218 - 82 5.7795 1.9862 0.5830 -0.2260 0.0030 -0.1467 -0.1138 -0.0022 0.0000 -0.0045 0.0202 0.211 - 83 6.0570 1.8764 0.5012 -0.2004 0.0025 -0.1378 -0.1068 -0.0020 0.0000 -0.0053 0.0181 0.201 - 84 6.3069 1.7776 0.4225 -0.1751 0.0021 -0.1271 -0.0985 -0.0019 0.0000 -0.0061 0.0157 0.188 - 85 6.5264 1.6907 0.3478 -0.1502 0.0017 -0.1146 -0.0889 -0.0018 0.0000 -0.0067 0.0131 0.174 - 86 6.7314 1.6096 0.3326 -0.1243 0.0014 -0.0996 -0.0772 -0.0016 0.0000 -0.0072 0.0103 0.157 - 87 6.9144 1.5372 0.2507 -0.0967 0.0011 -0.0812 -0.0629 -0.0014 0.0000 -0.0070 0.0073 0.138 - 88 7.0535 1.4822 0.1746 -0.0691 0.0010 -0.0601 -0.0466 -0.0012 0.0000 -0.0061 0.0047 0.120 - 89 7.1471 1.4451 0.1029 -0.0414 0.0008 -0.0370 -0.0287 -0.0009 0.0000 -0.0042 0.0025 0.104 - 90 7.1941 1.4265 0.0340 -0.0138 0.0008 -0.0125 -0.0097 -0.0005 0.0000 -0.0015 0.0008 0.097 + 61 0.0047 4.2713 0.0803 -0.4283 0.0134 -0.1293 -0.1003 0.0429 0.0000 0.0082 0.0281 0.332 + 62 0.0418 4.2566 0.2392 -0.4921 0.0130 -0.1491 -0.1156 0.0028 0.0000 0.0085 0.0316 0.324 + 63 0.1156 4.2274 0.3930 -0.4973 0.0125 -0.1517 -0.1176 -0.0001 0.0000 0.0083 0.0318 0.321 + 64 0.2254 4.1839 0.5386 -0.4985 0.0120 -0.1537 -0.1191 -0.0007 0.0000 0.0078 0.0317 0.315 + 65 0.3698 4.1268 0.6730 -0.4989 0.0115 -0.1559 -0.1209 -0.0009 0.0000 0.0070 0.0314 0.308 + 66 0.5474 4.0565 0.7936 -0.4984 0.0110 -0.1585 -0.1229 -0.0011 0.0000 0.0060 0.0310 0.299 + 67 0.7617 3.9717 0.9441 -0.4970 0.0105 -0.1614 -0.1251 -0.0013 0.0000 0.0050 0.0306 0.290 + 68 1.0116 3.8728 1.0344 -0.4945 0.0102 -0.1647 -0.1277 -0.0016 0.0000 0.0039 0.0302 0.281 + 69 1.2891 3.7630 1.1046 -0.4900 0.0101 -0.1680 -0.1302 -0.0018 0.0000 0.0029 0.0299 0.272 + 70 1.5912 3.6435 1.1542 -0.4833 0.0102 -0.1711 -0.1326 -0.0020 0.0000 0.0020 0.0297 0.265 + 71 1.9146 3.5155 1.1831 -0.4739 0.0104 -0.1739 -0.1348 -0.0022 0.0000 0.0012 0.0294 0.259 + 72 2.2558 3.3805 1.1921 -0.4619 0.0104 -0.1762 -0.1366 -0.0024 0.0000 0.0004 0.0292 0.253 + 73 2.6109 3.2400 1.1821 -0.4467 0.0100 -0.1778 -0.1379 -0.0025 0.0000 -0.0002 0.0289 0.249 + 74 2.9762 3.0955 1.1548 -0.4286 0.0092 -0.1786 -0.1385 -0.0026 0.0000 -0.0007 0.0286 0.245 + 75 3.3476 2.9485 1.1122 -0.4080 0.0083 -0.1785 -0.1384 -0.0026 0.0000 -0.0012 0.0282 0.241 + 76 3.7210 2.8008 1.0564 -0.3850 0.0074 -0.1773 -0.1375 -0.0026 0.0000 -0.0016 0.0277 0.239 + 77 4.0924 2.6538 0.9900 -0.3604 0.0065 -0.1752 -0.1358 -0.0026 0.0000 -0.0019 0.0270 0.236 + 78 4.4577 2.5093 0.9155 -0.3345 0.0056 -0.1720 -0.1333 -0.0026 0.0000 -0.0023 0.0262 0.233 + 79 4.8128 2.3687 0.8353 -0.3080 0.0049 -0.1677 -0.1300 -0.0025 0.0000 -0.0027 0.0251 0.229 + 80 5.1540 2.2338 0.7518 -0.2813 0.0042 -0.1624 -0.1259 -0.0024 0.0000 -0.0032 0.0238 0.224 + 81 5.4774 2.1058 0.6671 -0.2546 0.0036 -0.1560 -0.1209 -0.0023 0.0000 -0.0038 0.0223 0.218 + 82 5.7795 1.9862 0.5830 -0.2283 0.0030 -0.1483 -0.1150 -0.0022 0.0000 -0.0045 0.0204 0.211 + 83 6.0570 1.8764 0.5012 -0.2024 0.0025 -0.1391 -0.1078 -0.0021 0.0000 -0.0053 0.0183 0.201 + 84 6.3069 1.7776 0.4225 -0.1768 0.0021 -0.1283 -0.0994 -0.0019 0.0000 -0.0061 0.0158 0.188 + 85 6.5264 1.6907 0.3478 -0.1516 0.0017 -0.1157 -0.0897 -0.0018 0.0000 -0.0068 0.0132 0.174 + 86 6.7314 1.6096 0.3326 -0.1254 0.0014 -0.1005 -0.0779 -0.0016 0.0000 -0.0072 0.0104 0.157 + 87 6.9144 1.5372 0.2507 -0.0975 0.0012 -0.0818 -0.0634 -0.0014 0.0000 -0.0071 0.0074 0.138 + 88 7.0535 1.4822 0.1746 -0.0696 0.0010 -0.0606 -0.0470 -0.0012 0.0000 -0.0061 0.0047 0.120 + 89 7.1471 1.4451 0.1029 -0.0418 0.0008 -0.0373 -0.0289 -0.0009 0.0000 -0.0042 0.0025 0.105 + 90 7.1941 1.4265 0.0340 -0.0139 0.0008 -0.0126 -0.0098 -0.0005 0.0000 -0.0015 0.0008 0.097 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.02033 Clsurf = -0.00193 - CYsurf = -0.00327 Cmsurf = 0.09762 - CDsurf = -0.00029 Cnsurf = 0.00197 - CDisurf = -0.00029 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.02059 Clsurf = -0.00195 + CYsurf = -0.00332 Cmsurf = 0.09888 + CDsurf = -0.00030 Cnsurf = 0.00200 + CDisurf = -0.00030 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.12393 CDsurf = -0.00175 + CLsurf = -0.12555 CDsurf = -0.00180 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.4234 0.0133 -0.1279 -0.0991 0.0417 0.0000 0.0081 -0.0277 0.332 - 92 -0.0418 4.2566 0.2392 -0.4854 0.0129 -0.1471 -0.1140 0.0028 0.0000 0.0084 -0.0312 0.324 - 93 -0.1156 4.2274 0.3930 -0.4904 0.0124 -0.1496 -0.1160 -0.0001 0.0000 0.0082 -0.0314 0.321 - 94 -0.2254 4.1839 0.5386 -0.4916 0.0119 -0.1516 -0.1175 -0.0007 0.0000 0.0077 -0.0313 0.315 - 95 -0.3698 4.1268 0.6730 -0.4921 0.0114 -0.1538 -0.1192 -0.0009 0.0000 0.0069 -0.0310 0.308 - 96 -0.5474 4.0565 0.7936 -0.4915 0.0108 -0.1563 -0.1212 -0.0011 0.0000 0.0059 -0.0306 0.299 - 97 -0.7617 3.9717 0.9441 -0.4901 0.0104 -0.1592 -0.1234 -0.0013 0.0000 0.0049 -0.0302 0.290 - 98 -1.0116 3.8728 1.0344 -0.4875 0.0101 -0.1624 -0.1259 -0.0015 0.0000 0.0039 -0.0298 0.281 - 99 -1.2891 3.7630 1.1046 -0.4831 0.0100 -0.1656 -0.1284 -0.0017 0.0000 0.0029 -0.0295 0.272 - 100 -1.5912 3.6435 1.1542 -0.4764 0.0101 -0.1687 -0.1308 -0.0019 0.0000 0.0020 -0.0293 0.265 - 101 -1.9146 3.5155 1.1831 -0.4674 0.0103 -0.1715 -0.1329 -0.0021 0.0000 0.0012 -0.0290 0.259 - 102 -2.2558 3.3805 1.1921 -0.4554 0.0102 -0.1738 -0.1347 -0.0023 0.0000 0.0004 -0.0288 0.253 - 103 -2.6109 3.2400 1.1821 -0.4406 0.0098 -0.1754 -0.1360 -0.0024 0.0000 -0.0002 -0.0285 0.249 - 104 -2.9762 3.0955 1.1548 -0.4228 0.0091 -0.1762 -0.1366 -0.0025 0.0000 -0.0007 -0.0282 0.245 - 105 -3.3476 2.9485 1.1122 -0.4025 0.0082 -0.1761 -0.1365 -0.0026 0.0000 -0.0011 -0.0278 0.242 - 106 -3.7210 2.8008 1.0564 -0.3800 0.0073 -0.1750 -0.1357 -0.0026 0.0000 -0.0015 -0.0273 0.239 - 107 -4.0924 2.6538 0.9900 -0.3558 0.0064 -0.1729 -0.1341 -0.0026 0.0000 -0.0019 -0.0267 0.236 - 108 -4.4577 2.5093 0.9155 -0.3304 0.0056 -0.1699 -0.1317 -0.0025 0.0000 -0.0023 -0.0259 0.233 - 109 -4.8128 2.3687 0.8353 -0.3045 0.0048 -0.1658 -0.1285 -0.0024 0.0000 -0.0027 -0.0249 0.229 - 110 -5.1540 2.2338 0.7518 -0.2782 0.0041 -0.1606 -0.1245 -0.0024 0.0000 -0.0032 -0.0236 0.224 - 111 -5.4774 2.1058 0.6671 -0.2519 0.0035 -0.1543 -0.1196 -0.0023 0.0000 -0.0038 -0.0221 0.218 - 112 -5.7795 1.9862 0.5830 -0.2260 0.0030 -0.1467 -0.1138 -0.0022 0.0000 -0.0045 -0.0202 0.211 - 113 -6.0570 1.8764 0.5012 -0.2004 0.0025 -0.1377 -0.1068 -0.0020 0.0000 -0.0053 -0.0181 0.201 - 114 -6.3069 1.7776 0.4225 -0.1751 0.0021 -0.1271 -0.0985 -0.0019 0.0000 -0.0061 -0.0157 0.188 - 115 -6.5264 1.6907 0.3478 -0.1502 0.0017 -0.1146 -0.0889 -0.0018 0.0000 -0.0067 -0.0131 0.174 - 116 -6.7314 1.6096 0.3326 -0.1243 0.0014 -0.0996 -0.0772 -0.0016 0.0000 -0.0072 -0.0103 0.157 - 117 -6.9144 1.5372 0.2507 -0.0967 0.0011 -0.0812 -0.0629 -0.0014 0.0000 -0.0070 -0.0073 0.138 - 118 -7.0535 1.4822 0.1746 -0.0691 0.0010 -0.0601 -0.0466 -0.0012 0.0000 -0.0061 -0.0047 0.120 - 119 -7.1471 1.4451 0.1029 -0.0414 0.0008 -0.0370 -0.0287 -0.0009 0.0000 -0.0042 -0.0025 0.104 - 120 -7.1941 1.4265 0.0340 -0.0138 0.0008 -0.0125 -0.0097 -0.0005 0.0000 -0.0015 -0.0008 0.097 + 91 -0.0047 4.2713 0.0803 -0.4283 0.0134 -0.1293 -0.1003 0.0429 0.0000 0.0082 -0.0281 0.332 + 92 -0.0418 4.2566 0.2392 -0.4921 0.0130 -0.1491 -0.1156 0.0028 0.0000 0.0085 -0.0316 0.324 + 93 -0.1156 4.2274 0.3930 -0.4973 0.0125 -0.1517 -0.1176 -0.0001 0.0000 0.0083 -0.0318 0.321 + 94 -0.2254 4.1839 0.5386 -0.4985 0.0120 -0.1537 -0.1191 -0.0007 0.0000 0.0078 -0.0317 0.315 + 95 -0.3698 4.1268 0.6730 -0.4989 0.0115 -0.1559 -0.1209 -0.0009 0.0000 0.0070 -0.0314 0.308 + 96 -0.5474 4.0565 0.7936 -0.4984 0.0110 -0.1585 -0.1229 -0.0011 0.0000 0.0060 -0.0310 0.299 + 97 -0.7617 3.9717 0.9441 -0.4970 0.0105 -0.1614 -0.1251 -0.0013 0.0000 0.0050 -0.0306 0.290 + 98 -1.0116 3.8728 1.0344 -0.4944 0.0102 -0.1647 -0.1277 -0.0016 0.0000 0.0039 -0.0302 0.281 + 99 -1.2891 3.7630 1.1046 -0.4900 0.0101 -0.1680 -0.1302 -0.0018 0.0000 0.0029 -0.0299 0.272 + 100 -1.5912 3.6435 1.1542 -0.4833 0.0102 -0.1711 -0.1326 -0.0020 0.0000 0.0020 -0.0297 0.265 + 101 -1.9146 3.5155 1.1831 -0.4739 0.0104 -0.1739 -0.1348 -0.0022 0.0000 0.0012 -0.0294 0.259 + 102 -2.2558 3.3805 1.1921 -0.4619 0.0104 -0.1762 -0.1366 -0.0024 0.0000 0.0004 -0.0292 0.253 + 103 -2.6109 3.2400 1.1821 -0.4467 0.0100 -0.1778 -0.1379 -0.0025 0.0000 -0.0002 -0.0289 0.249 + 104 -2.9762 3.0955 1.1548 -0.4286 0.0092 -0.1786 -0.1385 -0.0026 0.0000 -0.0007 -0.0286 0.245 + 105 -3.3476 2.9485 1.1122 -0.4080 0.0083 -0.1785 -0.1384 -0.0026 0.0000 -0.0012 -0.0282 0.241 + 106 -3.7210 2.8008 1.0564 -0.3850 0.0074 -0.1773 -0.1375 -0.0026 0.0000 -0.0016 -0.0277 0.239 + 107 -4.0924 2.6538 0.9900 -0.3604 0.0065 -0.1752 -0.1358 -0.0026 0.0000 -0.0019 -0.0270 0.236 + 108 -4.4577 2.5093 0.9155 -0.3345 0.0056 -0.1720 -0.1333 -0.0026 0.0000 -0.0023 -0.0262 0.233 + 109 -4.8128 2.3687 0.8353 -0.3080 0.0049 -0.1677 -0.1300 -0.0025 0.0000 -0.0027 -0.0251 0.229 + 110 -5.1540 2.2338 0.7518 -0.2813 0.0042 -0.1624 -0.1259 -0.0024 0.0000 -0.0032 -0.0238 0.224 + 111 -5.4774 2.1058 0.6671 -0.2546 0.0036 -0.1560 -0.1209 -0.0023 0.0000 -0.0038 -0.0223 0.218 + 112 -5.7795 1.9862 0.5830 -0.2283 0.0030 -0.1483 -0.1150 -0.0022 0.0000 -0.0045 -0.0204 0.211 + 113 -6.0570 1.8764 0.5012 -0.2024 0.0025 -0.1391 -0.1078 -0.0021 0.0000 -0.0053 -0.0183 0.201 + 114 -6.3069 1.7776 0.4225 -0.1768 0.0021 -0.1283 -0.0994 -0.0019 0.0000 -0.0061 -0.0158 0.188 + 115 -6.5264 1.6907 0.3478 -0.1516 0.0017 -0.1157 -0.0897 -0.0018 0.0000 -0.0068 -0.0132 0.174 + 116 -6.7314 1.6096 0.3326 -0.1254 0.0014 -0.1005 -0.0779 -0.0016 0.0000 -0.0072 -0.0104 0.157 + 117 -6.9144 1.5372 0.2507 -0.0975 0.0012 -0.0818 -0.0634 -0.0014 0.0000 -0.0071 -0.0074 0.138 + 118 -7.0535 1.4822 0.1746 -0.0696 0.0010 -0.0606 -0.0470 -0.0012 0.0000 -0.0061 -0.0047 0.120 + 119 -7.1471 1.4451 0.1029 -0.0418 0.0008 -0.0373 -0.0289 -0.0009 0.0000 -0.0042 -0.0025 0.105 + 120 -7.1941 1.4265 0.0340 -0.0139 0.0008 -0.0126 -0.0098 -0.0005 0.0000 -0.0015 -0.0008 0.097 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = -0.00000 - CYsurf = -0.00000 Cmsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00000 CDsurf = 0.00000 Cnsurf = 0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.438 - 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.329 - 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.216 - 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.126 - 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.052 - 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.991 - 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.933 - 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.873 - 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.809 - 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.727 - 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.667 - 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.628 - 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.593 - 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.555 - 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.517 - 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.481 - 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.447 - 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.418 - 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.388 - 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.367 - 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.341 + 121 0.0000 10.0347 0.6931 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.160 + 122 0.0000 9.8296 1.1101 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.128 + 123 0.0000 9.5266 1.4857 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 1.073 + 124 0.0000 9.1281 1.8040 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 1.017 + 125 0.0000 8.6377 2.0517 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.969 + 126 0.0000 8.0598 2.2181 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.928 + 127 0.0000 7.4000 2.2957 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.884 + 128 0.0000 6.6646 2.2808 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.838 + 129 0.0000 5.8609 2.1733 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.780 + 130 0.0000 4.9969 1.9773 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.706 + 131 0.0000 4.4389 1.6667 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.650 + 132 0.0000 4.2198 1.6478 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.617 + 133 0.0000 3.9932 1.6033 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.579 + 134 0.0000 3.7615 1.5362 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.541 + 135 0.0000 3.5271 1.4499 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.510 + 136 0.0000 3.2923 1.3482 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.479 + 137 0.0000 3.0597 1.2352 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.441 + 138 0.0000 2.8315 1.1147 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.410 + 139 0.0000 2.6103 0.9908 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.386 + 140 0.0000 2.3983 0.8670 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.358 + 141 0.0000 2.1977 0.7464 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.335 142 0.0000 2.0106 0.6318 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.319 - 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.301 - 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.279 - 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.255 - 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.232 - 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.212 - 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.191 - 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.178 - 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.165 + 143 0.0000 1.8390 0.5251 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.298 + 144 0.0000 1.6847 0.4276 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.275 + 145 0.0000 1.5493 0.3400 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.256 + 146 0.0000 1.4342 0.2622 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.226 + 147 0.0000 1.3407 0.1933 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.210 + 148 0.0000 1.2696 0.1322 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.189 + 149 0.0000 1.2218 0.0769 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.176 + 150 0.0000 1.1978 0.0252 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.163 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00509 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = -0.00697 - CDsurf = 0.00003 Cnsurf = 0.00000 + CLsurf = -0.00516 Clsurf = 0.00000 + CYsurf = -0.00000 Cmsurf = -0.00691 + CDsurf = 0.00003 Cnsurf = -0.00000 CDisurf = 0.00003 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00513 CDsurf = 0.00003 + CLsurf = -0.00520 CDsurf = 0.00003 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.1408 -0.0075 -0.0667 -0.0053 -0.0002 0.0000 0.0006 0.0003 0.368 - 152 -1.3090 31.2096 11.6724 -0.1821 -0.0030 -0.0228 -0.0058 -0.0000 0.0000 0.0004 0.0005 0.327 - 153 -0.9350 34.0626 12.7394 -0.1801 0.0178 -0.0129 -0.0053 0.0001 0.0000 -0.0001 0.0004 0.225 - 154 -0.5610 36.1619 13.5246 -0.1746 0.0273 -0.0081 -0.0048 0.0001 0.0000 -0.0005 0.0003 0.155 - 155 -0.1870 37.5332 14.0374 -0.1718 0.0309 -0.0053 -0.0046 0.0001 0.0000 -0.0006 0.0004 0.120 - 156 0.1870 37.5332 14.0374 -0.1718 0.0309 -0.0053 -0.0046 0.0001 0.0000 -0.0006 0.0004 0.120 - 157 0.5610 36.1619 13.5246 -0.1746 0.0273 -0.0081 -0.0048 0.0001 0.0000 -0.0005 0.0003 0.155 - 158 0.9350 34.0626 12.7394 -0.1801 0.0178 -0.0129 -0.0053 0.0001 0.0000 -0.0001 0.0004 0.225 - 159 1.3090 31.2096 11.6724 -0.1821 -0.0030 -0.0228 -0.0058 -0.0000 0.0000 0.0004 0.0005 0.327 - 160 1.6830 26.5957 9.9468 -0.1408 -0.0075 -0.0667 -0.0053 -0.0002 0.0000 0.0006 0.0003 0.368 + 151 -1.6830 26.5957 9.9468 -0.1428 -0.0076 -0.0677 -0.0054 -0.0002 0.0000 0.0007 0.0003 0.371 + 152 -1.3090 31.2096 11.6724 -0.1847 -0.0031 -0.0231 -0.0059 -0.0000 0.0000 0.0005 0.0005 0.330 + 153 -0.9350 34.0626 12.7394 -0.1826 0.0179 -0.0131 -0.0054 0.0001 0.0000 -0.0001 0.0004 0.229 + 154 -0.5610 36.1619 13.5246 -0.1770 0.0274 -0.0082 -0.0049 0.0001 0.0000 -0.0004 0.0003 0.159 + 155 -0.1870 37.5332 14.0374 -0.1741 0.0310 -0.0054 -0.0046 0.0001 0.0000 -0.0006 0.0004 0.125 + 156 0.1870 37.5332 14.0374 -0.1741 0.0310 -0.0054 -0.0046 0.0001 0.0000 -0.0006 0.0004 0.125 + 157 0.5610 36.1619 13.5246 -0.1770 0.0274 -0.0082 -0.0049 0.0001 0.0000 -0.0004 0.0003 0.159 + 158 0.9350 34.0626 12.7394 -0.1826 0.0179 -0.0131 -0.0054 0.0001 0.0000 -0.0001 0.0004 0.229 + 159 1.3090 31.2096 11.6724 -0.1847 -0.0031 -0.0231 -0.0059 -0.0000 0.0000 0.0005 0.0005 0.330 + 160 1.6830 26.5957 9.9468 -0.1428 -0.0076 -0.0677 -0.0054 -0.0002 0.0000 0.0007 0.0003 0.371 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = -0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = -0.00000 Cnsurf = -0.00000 - CDisurf = -0.00000 CDvsurf = 0.00000 + CDsurf = 0.00000 Cnsurf = -0.00000 + CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = 0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.623 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.773 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0001 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.764 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.755 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.749 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.736 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.708 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.654 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.550 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.485 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.336 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.800 + 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.781 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.772 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.766 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.745 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.712 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.647 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.507 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.456 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_06_03.txt b/regression/scripts/AVL/avl_files/strip_forces_case_06_03.txt index c2b2b00c34..1e6e8f5be3 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_06_03.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_06_03.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.24931 Clsurf = -0.04780 - CYsurf = -0.01757 Cmsurf = -0.22979 - CDsurf = 0.00575 Cnsurf = 0.00023 - CDisurf = 0.00575 CDvsurf = 0.00000 + CLsurf = 0.25030 Clsurf = -0.04789 + CYsurf = -0.01762 Cmsurf = -0.23029 + CDsurf = 0.00580 Cnsurf = 0.00023 + CDisurf = 0.00580 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.48783 CDsurf = 0.01123 + CLsurf = 0.48977 CDsurf = 0.01131 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 3.3801 0.0926 0.5462 0.4231 0.3768 0.0000 -0.0381 -0.1201 0.340 - 2 0.1025 7.6885 1.0492 3.1045 0.0920 0.5187 0.4018 0.0645 0.0000 -0.0366 -0.1123 0.341 - 3 0.2837 7.5620 1.7073 3.0789 0.0905 0.5240 0.4059 0.0434 0.0000 -0.0355 -0.1121 0.338 - 4 0.5530 7.3741 2.3052 3.0614 0.0877 0.5345 0.4141 0.0385 0.0000 -0.0335 -0.1122 0.331 - 5 0.9075 7.1267 2.8223 3.0329 0.0835 0.5481 0.4246 0.0353 0.0000 -0.0311 -0.1123 0.323 - 6 1.3432 6.8226 3.2414 2.9854 0.0780 0.5639 0.4368 0.0302 0.0000 -0.0288 -0.1129 0.316 - 7 1.8554 6.4651 3.5491 2.9169 0.0722 0.5816 0.4505 0.0262 0.0000 -0.0270 -0.1142 0.310 - 8 2.4386 6.0582 3.7368 2.8192 0.0655 0.6001 0.4648 0.0224 0.0000 -0.0260 -0.1163 0.306 - 9 3.0862 5.6062 3.8005 2.6902 0.0556 0.6192 0.4796 0.0153 0.0000 -0.0262 -0.1194 0.305 - 10 3.7613 5.1351 3.4440 2.5474 0.0451 0.6403 0.4960 0.0125 0.0000 -0.0276 -0.1239 0.306 - 11 4.4532 4.6522 3.3149 2.3850 0.0343 0.6620 0.5128 0.0053 0.0000 -0.0305 -0.1296 0.310 - 12 5.1831 4.1429 3.0930 2.2115 0.0187 0.6896 0.5342 -0.0016 0.0000 -0.0342 -0.1369 0.314 - 13 6.0123 3.7903 3.4706 2.0438 0.0088 0.6592 0.5397 -0.0045 0.0000 -0.0345 -0.1511 0.314 - 14 6.9353 3.6075 3.3775 1.9154 0.0114 0.6490 0.5314 -0.0033 0.0000 -0.0340 -0.1488 0.314 - 15 7.8737 3.4215 3.2389 1.8021 0.0124 0.6438 0.5271 -0.0030 0.0000 -0.0334 -0.1473 0.313 - 16 8.8172 3.2345 3.0619 1.6970 0.0131 0.6413 0.5251 -0.0031 0.0000 -0.0329 -0.1463 0.313 - 17 9.7556 3.0486 2.8543 1.5970 0.0137 0.6404 0.5243 -0.0033 0.0000 -0.0323 -0.1457 0.312 - 18 10.6786 2.8657 2.6240 1.5011 0.0145 0.6403 0.5243 -0.0035 0.0000 -0.0318 -0.1452 0.311 - 19 11.5760 2.6879 2.3787 1.4073 0.0156 0.6400 0.5240 -0.0038 0.0000 -0.0311 -0.1445 0.309 - 20 12.4328 2.5181 2.1010 1.3149 0.0172 0.6384 0.5226 -0.0041 0.0000 -0.0300 -0.1433 0.307 - 21 13.2400 2.3582 1.8520 1.2226 0.0194 0.6338 0.5189 -0.0044 0.0000 -0.0285 -0.1411 0.305 - 22 13.9941 2.2087 1.6074 1.1276 0.0222 0.6241 0.5110 -0.0048 0.0000 -0.0262 -0.1373 0.301 - 23 14.6868 2.0715 1.3716 1.0273 0.0257 0.6063 0.4964 -0.0051 0.0000 -0.0230 -0.1311 0.296 - 24 15.3105 1.9479 1.1479 0.9186 0.0296 0.5766 0.4720 -0.0053 0.0000 -0.0189 -0.1221 0.290 - 25 15.8583 1.8393 0.9381 0.7982 0.0336 0.5306 0.4344 -0.0052 0.0000 -0.0152 -0.1105 0.285 - 26 16.3244 1.7470 0.7427 0.6650 0.0382 0.4654 0.3810 -0.0037 0.0000 -0.0153 -0.0986 0.290 - 27 16.6722 1.4928 0.4131 0.5245 0.0426 1.1838 0.3520 -0.0133 0.0000 -0.0136 -0.0482 0.289 - 28 16.9098 1.1466 0.2292 0.3840 0.0482 1.1296 0.3359 -0.0227 0.0000 0.0038 -0.0382 0.239 - 29 17.0696 0.9138 0.1104 0.2349 0.0521 0.8684 0.2582 -0.0299 0.0000 0.0193 -0.0217 0.175 - 30 17.1499 0.7967 0.0322 0.0791 0.0538 0.3363 0.1000 -0.0205 0.0000 0.0128 -0.0059 0.122 + 1 0.0114 7.7520 0.3539 3.4065 0.0921 0.5505 0.4264 0.3796 0.0000 -0.0402 -0.1225 0.344 + 2 0.1025 7.6885 1.0491 3.1247 0.0915 0.5221 0.4044 0.0647 0.0000 -0.0382 -0.1142 0.345 + 3 0.2837 7.5620 1.7073 3.0987 0.0903 0.5274 0.4085 0.0432 0.0000 -0.0371 -0.1140 0.341 + 4 0.5530 7.3741 2.3052 3.0813 0.0879 0.5381 0.4168 0.0376 0.0000 -0.0352 -0.1141 0.334 + 5 0.9075 7.1267 2.8223 3.0539 0.0840 0.5520 0.4276 0.0349 0.0000 -0.0329 -0.1143 0.327 + 6 1.3432 6.8226 3.2414 3.0088 0.0786 0.5682 0.4402 0.0319 0.0000 -0.0306 -0.1150 0.319 + 7 1.8554 6.4651 3.5491 2.9387 0.0731 0.5859 0.4539 0.0270 0.0000 -0.0287 -0.1163 0.313 + 8 2.4386 6.0582 3.7368 2.8404 0.0666 0.6046 0.4684 0.0223 0.0000 -0.0277 -0.1184 0.309 + 9 3.0862 5.6062 3.8005 2.7131 0.0574 0.6244 0.4837 0.0165 0.0000 -0.0278 -0.1216 0.308 + 10 3.7613 5.1351 3.4440 2.5745 0.0466 0.6472 0.5013 0.0108 0.0000 -0.0284 -0.1256 0.307 + 11 4.4532 4.6522 3.3149 2.3940 0.0343 0.6645 0.5147 0.0062 0.0000 -0.0299 -0.1295 0.308 + 12 5.1831 4.1429 3.0930 2.2172 0.0175 0.6914 0.5356 -0.0019 0.0000 -0.0328 -0.1361 0.311 + 13 6.0123 3.7903 3.4706 2.0491 0.0083 0.6609 0.5411 -0.0044 0.0000 -0.0325 -0.1496 0.310 + 14 6.9353 3.6075 3.3775 1.9196 0.0111 0.6505 0.5325 -0.0033 0.0000 -0.0317 -0.1470 0.310 + 15 7.8737 3.4215 3.2389 1.8053 0.0122 0.6450 0.5281 -0.0030 0.0000 -0.0310 -0.1453 0.309 + 16 8.8172 3.2345 3.0619 1.6996 0.0129 0.6423 0.5259 -0.0031 0.0000 -0.0303 -0.1442 0.308 + 17 9.7556 3.0486 2.8543 1.5993 0.0136 0.6413 0.5250 -0.0033 0.0000 -0.0297 -0.1435 0.307 + 18 10.6786 2.8657 2.6239 1.5030 0.0144 0.6411 0.5249 -0.0036 0.0000 -0.0291 -0.1430 0.305 + 19 11.5760 2.6879 2.3787 1.4088 0.0156 0.6407 0.5246 -0.0039 0.0000 -0.0284 -0.1422 0.304 + 20 12.4328 2.5181 2.1010 1.3162 0.0172 0.6390 0.5232 -0.0042 0.0000 -0.0274 -0.1410 0.302 + 21 13.2400 2.3582 1.8520 1.2235 0.0193 0.6343 0.5193 -0.0045 0.0000 -0.0258 -0.1388 0.300 + 22 13.9941 2.2087 1.6074 1.1283 0.0222 0.6245 0.5113 -0.0049 0.0000 -0.0235 -0.1350 0.296 + 23 14.6868 2.0715 1.3716 1.0276 0.0257 0.6065 0.4966 -0.0052 0.0000 -0.0203 -0.1288 0.291 + 24 15.3105 1.9479 1.1479 0.9184 0.0295 0.5765 0.4720 -0.0054 0.0000 -0.0162 -0.1197 0.284 + 25 15.8583 1.8393 0.9381 0.7977 0.0335 0.5303 0.4341 -0.0053 0.0000 -0.0126 -0.1080 0.279 + 26 16.3244 1.7470 0.7427 0.6636 0.0375 0.4644 0.3802 -0.0038 0.0000 -0.0126 -0.0960 0.283 + 27 16.6722 1.4928 0.4131 0.5233 0.0420 1.1811 0.3512 -0.0136 0.0000 -0.0115 -0.0471 0.283 + 28 16.9098 1.1466 0.2292 0.3833 0.0479 1.1274 0.3353 -0.0229 0.0000 0.0056 -0.0372 0.233 + 29 17.0696 0.9138 0.1104 0.2345 0.0520 0.8670 0.2578 -0.0302 0.0000 0.0205 -0.0211 0.170 + 30 17.1499 0.7967 0.0322 0.0790 0.0545 0.3361 0.1000 -0.0209 0.0000 0.0132 -0.0057 0.118 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.24930 Clsurf = 0.04780 - CYsurf = 0.01757 Cmsurf = -0.22979 - CDsurf = 0.00575 Cnsurf = -0.00023 - CDisurf = 0.00575 CDvsurf = 0.00000 + CLsurf = 0.25030 Clsurf = 0.04789 + CYsurf = 0.01762 Cmsurf = -0.23029 + CDsurf = 0.00580 Cnsurf = -0.00023 + CDisurf = 0.00580 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.48783 CDsurf = 0.01123 + CLsurf = 0.48977 CDsurf = 0.01131 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 3.3801 0.0926 0.5462 0.4231 0.3768 0.0000 -0.0381 0.1201 0.340 - 32 -0.1025 7.6885 1.0492 3.1045 0.0920 0.5187 0.4018 0.0645 0.0000 -0.0366 0.1123 0.341 - 33 -0.2837 7.5620 1.7073 3.0789 0.0905 0.5240 0.4059 0.0434 0.0000 -0.0355 0.1121 0.338 - 34 -0.5530 7.3741 2.3052 3.0614 0.0877 0.5345 0.4141 0.0385 0.0000 -0.0335 0.1122 0.331 - 35 -0.9075 7.1267 2.8223 3.0329 0.0835 0.5481 0.4246 0.0353 0.0000 -0.0311 0.1123 0.323 - 36 -1.3432 6.8226 3.2414 2.9854 0.0780 0.5639 0.4368 0.0302 0.0000 -0.0288 0.1129 0.316 - 37 -1.8554 6.4651 3.5491 2.9169 0.0722 0.5816 0.4505 0.0262 0.0000 -0.0270 0.1142 0.310 - 38 -2.4386 6.0582 3.7368 2.8191 0.0655 0.6001 0.4648 0.0224 0.0000 -0.0260 0.1163 0.306 - 39 -3.0862 5.6062 3.8005 2.6902 0.0556 0.6192 0.4796 0.0153 0.0000 -0.0262 0.1194 0.305 - 40 -3.7613 5.1351 3.4440 2.5474 0.0451 0.6403 0.4960 0.0125 0.0000 -0.0276 0.1239 0.306 - 41 -4.4532 4.6522 3.3149 2.3850 0.0343 0.6620 0.5128 0.0053 0.0000 -0.0305 0.1296 0.310 - 42 -5.1831 4.1429 3.0930 2.2114 0.0187 0.6896 0.5342 -0.0016 0.0000 -0.0342 0.1369 0.314 - 43 -6.0123 3.7903 3.4706 2.0438 0.0088 0.6592 0.5397 -0.0045 0.0000 -0.0345 0.1510 0.314 - 44 -6.9353 3.6075 3.3775 1.9154 0.0114 0.6490 0.5314 -0.0033 0.0000 -0.0340 0.1488 0.314 - 45 -7.8737 3.4215 3.2389 1.8021 0.0124 0.6438 0.5271 -0.0030 0.0000 -0.0334 0.1473 0.313 - 46 -8.8172 3.2345 3.0619 1.6969 0.0131 0.6413 0.5251 -0.0031 0.0000 -0.0329 0.1463 0.313 - 47 -9.7556 3.0486 2.8543 1.5970 0.0137 0.6403 0.5243 -0.0033 0.0000 -0.0323 0.1457 0.312 - 48 -10.6786 2.8657 2.6240 1.5011 0.0145 0.6403 0.5243 -0.0035 0.0000 -0.0318 0.1452 0.311 - 49 -11.5760 2.6879 2.3787 1.4072 0.0156 0.6400 0.5240 -0.0038 0.0000 -0.0310 0.1445 0.309 - 50 -12.4328 2.5181 2.1010 1.3149 0.0172 0.6384 0.5226 -0.0041 0.0000 -0.0300 0.1433 0.307 - 51 -13.2400 2.3582 1.8520 1.2225 0.0194 0.6338 0.5189 -0.0044 0.0000 -0.0285 0.1411 0.305 - 52 -13.9941 2.2087 1.6074 1.1276 0.0222 0.6241 0.5110 -0.0048 0.0000 -0.0262 0.1373 0.301 - 53 -14.6868 2.0715 1.3716 1.0273 0.0257 0.6063 0.4964 -0.0051 0.0000 -0.0230 0.1311 0.296 - 54 -15.3105 1.9479 1.1479 0.9185 0.0296 0.5765 0.4720 -0.0053 0.0000 -0.0189 0.1221 0.290 - 55 -15.8583 1.8393 0.9381 0.7982 0.0336 0.5306 0.4344 -0.0052 0.0000 -0.0152 0.1105 0.285 - 56 -16.3244 1.7470 0.7427 0.6650 0.0382 0.4653 0.3810 -0.0037 0.0000 -0.0153 0.0986 0.290 - 57 -16.6722 1.4928 0.4131 0.5245 0.0425 1.1838 0.3520 -0.0133 0.0000 -0.0136 0.0482 0.289 - 58 -16.9098 1.1466 0.2292 0.3840 0.0482 1.1296 0.3359 -0.0227 0.0000 0.0038 0.0382 0.239 - 59 -17.0696 0.9138 0.1104 0.2349 0.0521 0.8684 0.2582 -0.0299 0.0000 0.0193 0.0217 0.175 - 60 -17.1499 0.7967 0.0322 0.0791 0.0538 0.3363 0.1000 -0.0205 0.0000 0.0128 0.0059 0.122 + 31 -0.0114 7.7520 0.3539 3.4065 0.0920 0.5505 0.4264 0.3796 0.0000 -0.0402 0.1225 0.344 + 32 -0.1025 7.6885 1.0491 3.1247 0.0915 0.5221 0.4044 0.0647 0.0000 -0.0382 0.1142 0.345 + 33 -0.2837 7.5620 1.7073 3.0987 0.0903 0.5274 0.4085 0.0432 0.0000 -0.0371 0.1140 0.341 + 34 -0.5530 7.3741 2.3052 3.0813 0.0879 0.5381 0.4168 0.0376 0.0000 -0.0352 0.1141 0.334 + 35 -0.9075 7.1267 2.8223 3.0539 0.0840 0.5520 0.4276 0.0349 0.0000 -0.0329 0.1143 0.327 + 36 -1.3432 6.8226 3.2414 3.0088 0.0786 0.5682 0.4402 0.0319 0.0000 -0.0306 0.1150 0.319 + 37 -1.8554 6.4651 3.5491 2.9387 0.0731 0.5859 0.4539 0.0270 0.0000 -0.0287 0.1163 0.313 + 38 -2.4386 6.0582 3.7368 2.8404 0.0666 0.6046 0.4684 0.0223 0.0000 -0.0277 0.1184 0.309 + 39 -3.0862 5.6062 3.8005 2.7131 0.0574 0.6244 0.4837 0.0165 0.0000 -0.0278 0.1216 0.308 + 40 -3.7613 5.1351 3.4440 2.5745 0.0466 0.6472 0.5013 0.0108 0.0000 -0.0284 0.1256 0.307 + 41 -4.4532 4.6522 3.3149 2.3940 0.0343 0.6645 0.5147 0.0062 0.0000 -0.0299 0.1295 0.308 + 42 -5.1831 4.1429 3.0930 2.2172 0.0175 0.6914 0.5356 -0.0019 0.0000 -0.0328 0.1361 0.311 + 43 -6.0123 3.7903 3.4706 2.0491 0.0083 0.6609 0.5411 -0.0044 0.0000 -0.0325 0.1496 0.310 + 44 -6.9353 3.6075 3.3775 1.9196 0.0111 0.6505 0.5325 -0.0033 0.0000 -0.0317 0.1470 0.310 + 45 -7.8737 3.4215 3.2389 1.8053 0.0122 0.6450 0.5281 -0.0030 0.0000 -0.0310 0.1453 0.309 + 46 -8.8172 3.2345 3.0619 1.6996 0.0129 0.6423 0.5259 -0.0031 0.0000 -0.0303 0.1442 0.308 + 47 -9.7556 3.0486 2.8543 1.5993 0.0136 0.6413 0.5250 -0.0033 0.0000 -0.0297 0.1435 0.307 + 48 -10.6786 2.8657 2.6239 1.5030 0.0144 0.6411 0.5249 -0.0036 0.0000 -0.0291 0.1430 0.305 + 49 -11.5760 2.6879 2.3787 1.4088 0.0156 0.6407 0.5246 -0.0039 0.0000 -0.0284 0.1422 0.304 + 50 -12.4328 2.5181 2.1010 1.3162 0.0172 0.6390 0.5232 -0.0042 0.0000 -0.0274 0.1410 0.302 + 51 -13.2400 2.3582 1.8520 1.2235 0.0193 0.6343 0.5193 -0.0045 0.0000 -0.0258 0.1388 0.300 + 52 -13.9941 2.2087 1.6074 1.1283 0.0222 0.6245 0.5113 -0.0049 0.0000 -0.0235 0.1350 0.296 + 53 -14.6868 2.0715 1.3716 1.0276 0.0257 0.6065 0.4966 -0.0052 0.0000 -0.0203 0.1288 0.291 + 54 -15.3105 1.9479 1.1479 0.9184 0.0295 0.5765 0.4720 -0.0054 0.0000 -0.0162 0.1197 0.284 + 55 -15.8583 1.8393 0.9381 0.7977 0.0335 0.5303 0.4341 -0.0053 0.0000 -0.0126 0.1080 0.279 + 56 -16.3244 1.7470 0.7427 0.6636 0.0375 0.4644 0.3802 -0.0038 0.0000 -0.0126 0.0960 0.283 + 57 -16.6722 1.4928 0.4131 0.5233 0.0420 1.1811 0.3512 -0.0136 0.0000 -0.0115 0.0471 0.283 + 58 -16.9098 1.1466 0.2292 0.3833 0.0479 1.1274 0.3353 -0.0229 0.0000 0.0056 0.0372 0.233 + 59 -17.0696 0.9138 0.1104 0.2345 0.0520 0.8670 0.2578 -0.0302 0.0000 0.0205 0.0211 0.170 + 60 -17.1499 0.7967 0.0322 0.0790 0.0545 0.3361 0.1000 -0.0209 0.0000 0.0132 0.0057 0.118 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.00170 Clsurf = 0.00003 - CYsurf = 0.00028 Cmsurf = 0.00747 - CDsurf = -0.00007 Cnsurf = -0.00015 - CDisurf = -0.00007 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.00196 Clsurf = 0.00005 + CYsurf = 0.00033 Cmsurf = 0.00873 + CDsurf = -0.00008 Cnsurf = -0.00018 + CDisurf = -0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.01035 CDsurf = -0.00042 + CLsurf = -0.01195 CDsurf = -0.00048 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 -0.0886 0.0499 -0.0269 -0.0208 0.0009 0.0000 0.0004 0.0048 0.269 - 62 0.0418 4.2566 0.2392 -0.0909 0.0497 -0.0277 -0.0214 -0.0006 0.0000 0.0004 0.0049 0.267 - 63 0.1156 4.2274 0.3930 -0.0911 0.0494 -0.0279 -0.0215 -0.0008 0.0000 0.0003 0.0048 0.264 - 64 0.2254 4.1839 0.5386 -0.0911 0.0489 -0.0282 -0.0218 -0.0008 0.0000 0.0002 0.0048 0.258 - 65 0.3698 4.1268 0.6730 -0.0910 0.0481 -0.0286 -0.0220 -0.0008 0.0000 -0.0000 0.0047 0.249 - 66 0.5474 4.0565 0.7936 -0.0908 0.0471 -0.0290 -0.0224 -0.0008 0.0000 -0.0002 0.0046 0.239 - 67 0.7617 3.9717 0.9441 -0.0901 0.0458 -0.0294 -0.0227 -0.0008 0.0000 -0.0005 0.0044 0.228 - 68 1.0116 3.8728 1.0344 -0.0890 0.0442 -0.0298 -0.0230 -0.0009 0.0000 -0.0008 0.0043 0.217 - 69 1.2891 3.7630 1.1046 -0.0869 0.0425 -0.0299 -0.0231 -0.0009 0.0000 -0.0010 0.0041 0.206 - 70 1.5912 3.6435 1.1542 -0.0837 0.0407 -0.0298 -0.0230 -0.0009 0.0000 -0.0013 0.0038 0.195 - 71 1.9146 3.5155 1.1831 -0.0789 0.0389 -0.0291 -0.0224 -0.0009 0.0000 -0.0015 0.0035 0.184 - 72 2.2558 3.3805 1.1921 -0.0724 0.0373 -0.0278 -0.0214 -0.0008 0.0000 -0.0017 0.0032 0.172 - 73 2.6109 3.2400 1.1821 -0.0641 0.0357 -0.0256 -0.0198 -0.0008 0.0000 -0.0018 0.0027 0.159 - 74 2.9762 3.0955 1.1548 -0.0540 0.0342 -0.0226 -0.0174 -0.0007 0.0000 -0.0018 0.0022 0.144 - 75 3.3476 2.9485 1.1122 -0.0424 0.0330 -0.0186 -0.0144 -0.0006 0.0000 -0.0018 0.0015 0.122 - 76 3.7210 2.8008 1.0564 -0.0298 0.0319 -0.0138 -0.0106 -0.0004 0.0000 -0.0017 0.0008 0.086 - 77 4.0924 2.6538 0.9900 -0.0168 0.0311 -0.0082 -0.0063 -0.0002 0.0000 -0.0016 0.0000 0.001 - 78 4.4577 2.5093 0.9155 -0.0040 0.0305 -0.0020 -0.0016 -0.0001 0.0000 -0.0013 -0.0008 -0.594 - 79 4.8128 2.3687 0.8353 0.0081 0.0301 0.0044 0.0034 0.0001 0.0000 -0.0010 -0.0016 0.545 - 80 5.1540 2.2338 0.7518 0.0187 0.0299 0.0108 0.0084 0.0003 0.0000 -0.0006 -0.0023 0.321 - 81 5.4774 2.1058 0.6671 0.0275 0.0299 0.0169 0.0130 0.0004 0.0000 -0.0001 -0.0029 0.258 - 82 5.7795 1.9862 0.5830 0.0340 0.0300 0.0222 0.0171 0.0006 0.0000 0.0005 -0.0033 0.224 - 83 6.0570 1.8764 0.5012 0.0383 0.0301 0.0264 0.0204 0.0006 0.0000 0.0011 -0.0034 0.198 - 84 6.3069 1.7776 0.4225 0.0401 0.0303 0.0292 0.0225 0.0007 0.0000 0.0017 -0.0034 0.175 - 85 6.5264 1.6907 0.3478 0.0396 0.0305 0.0303 0.0234 0.0007 0.0000 0.0022 -0.0031 0.154 - 86 6.7314 1.6096 0.3326 0.0369 0.0306 0.0297 0.0229 0.0006 0.0000 0.0027 -0.0026 0.132 - 87 6.9144 1.5372 0.2507 0.0315 0.0308 0.0266 0.0205 0.0005 0.0000 0.0029 -0.0019 0.109 - 88 7.0535 1.4822 0.1746 0.0240 0.0309 0.0210 0.0162 0.0004 0.0000 0.0026 -0.0012 0.088 - 89 7.1471 1.4451 0.1029 0.0150 0.0310 0.0135 0.0104 0.0002 0.0000 0.0019 -0.0007 0.072 - 90 7.1941 1.4265 0.0340 0.0051 0.0310 0.0047 0.0036 0.0000 0.0000 0.0007 -0.0002 0.063 + 61 0.0047 4.2713 0.0803 -0.0951 0.0500 -0.0289 -0.0223 0.0011 0.0000 0.0005 0.0052 0.273 + 62 0.0418 4.2566 0.2392 -0.0978 0.0499 -0.0298 -0.0230 -0.0007 0.0000 0.0005 0.0053 0.271 + 63 0.1156 4.2274 0.3930 -0.0980 0.0495 -0.0300 -0.0232 -0.0008 0.0000 0.0004 0.0053 0.267 + 64 0.2254 4.1839 0.5386 -0.0980 0.0490 -0.0304 -0.0234 -0.0008 0.0000 0.0003 0.0052 0.261 + 65 0.3698 4.1268 0.6730 -0.0979 0.0482 -0.0308 -0.0237 -0.0009 0.0000 0.0001 0.0051 0.253 + 66 0.5474 4.0565 0.7936 -0.0977 0.0472 -0.0312 -0.0241 -0.0009 0.0000 -0.0002 0.0050 0.243 + 67 0.7617 3.9717 0.9441 -0.0970 0.0459 -0.0317 -0.0244 -0.0009 0.0000 -0.0004 0.0048 0.232 + 68 1.0116 3.8728 1.0344 -0.0958 0.0443 -0.0321 -0.0247 -0.0009 0.0000 -0.0007 0.0047 0.221 + 69 1.2891 3.7630 1.1046 -0.0937 0.0426 -0.0323 -0.0249 -0.0010 0.0000 -0.0010 0.0045 0.210 + 70 1.5912 3.6435 1.1542 -0.0904 0.0408 -0.0321 -0.0248 -0.0010 0.0000 -0.0013 0.0042 0.199 + 71 1.9146 3.5155 1.1831 -0.0855 0.0391 -0.0315 -0.0243 -0.0010 0.0000 -0.0015 0.0039 0.189 + 72 2.2558 3.3805 1.1921 -0.0788 0.0374 -0.0302 -0.0233 -0.0009 0.0000 -0.0017 0.0036 0.178 + 73 2.6109 3.2400 1.1821 -0.0702 0.0358 -0.0281 -0.0216 -0.0009 0.0000 -0.0018 0.0031 0.166 + 74 2.9762 3.0955 1.1548 -0.0597 0.0344 -0.0250 -0.0193 -0.0008 0.0000 -0.0019 0.0025 0.153 + 75 3.3476 2.9485 1.1122 -0.0478 0.0331 -0.0210 -0.0162 -0.0006 0.0000 -0.0019 0.0019 0.134 + 76 3.7210 2.8008 1.0564 -0.0347 0.0320 -0.0161 -0.0124 -0.0005 0.0000 -0.0018 0.0011 0.106 + 77 4.0924 2.6538 0.9900 -0.0212 0.0312 -0.0104 -0.0080 -0.0003 0.0000 -0.0016 0.0003 0.048 + 78 4.4577 2.5093 0.9155 -0.0079 0.0305 -0.0041 -0.0032 -0.0001 0.0000 -0.0014 -0.0005 -0.185 + 79 4.8128 2.3687 0.8353 0.0046 0.0301 0.0025 0.0019 0.0001 0.0000 -0.0010 -0.0013 0.791 + 80 5.1540 2.2338 0.7518 0.0157 0.0299 0.0091 0.0070 0.0002 0.0000 -0.0006 -0.0020 0.341 + 81 5.4774 2.1058 0.6671 0.0248 0.0299 0.0153 0.0118 0.0004 0.0000 -0.0001 -0.0026 0.263 + 82 5.7795 1.9862 0.5830 0.0318 0.0300 0.0208 0.0160 0.0005 0.0000 0.0004 -0.0031 0.224 + 83 6.0570 1.8764 0.5012 0.0364 0.0301 0.0251 0.0194 0.0006 0.0000 0.0010 -0.0033 0.197 + 84 6.3069 1.7776 0.4225 0.0385 0.0303 0.0281 0.0216 0.0006 0.0000 0.0016 -0.0032 0.175 + 85 6.5264 1.6907 0.3478 0.0383 0.0305 0.0293 0.0226 0.0007 0.0000 0.0022 -0.0030 0.153 + 86 6.7314 1.6096 0.3326 0.0358 0.0306 0.0288 0.0222 0.0006 0.0000 0.0027 -0.0025 0.131 + 87 6.9144 1.5372 0.2507 0.0307 0.0308 0.0259 0.0200 0.0005 0.0000 0.0028 -0.0019 0.108 + 88 7.0535 1.4822 0.1746 0.0235 0.0309 0.0205 0.0158 0.0004 0.0000 0.0026 -0.0012 0.087 + 89 7.1471 1.4451 0.1029 0.0147 0.0310 0.0132 0.0102 0.0002 0.0000 0.0018 -0.0006 0.070 + 90 7.1941 1.4265 0.0340 0.0050 0.0311 0.0046 0.0035 0.0000 0.0000 0.0007 -0.0002 0.062 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = -0.00170 Clsurf = -0.00003 - CYsurf = -0.00028 Cmsurf = 0.00747 - CDsurf = -0.00007 Cnsurf = 0.00015 - CDisurf = -0.00007 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = -0.00196 Clsurf = -0.00005 + CYsurf = -0.00033 Cmsurf = 0.00873 + CDsurf = -0.00008 Cnsurf = 0.00018 + CDisurf = -0.00008 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.01035 CDsurf = -0.00042 + CLsurf = -0.01195 CDsurf = -0.00048 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 -0.0886 0.0499 -0.0269 -0.0208 0.0009 0.0000 0.0004 -0.0048 0.269 - 92 -0.0418 4.2566 0.2392 -0.0909 0.0497 -0.0277 -0.0214 -0.0006 0.0000 0.0004 -0.0049 0.267 - 93 -0.1156 4.2274 0.3930 -0.0911 0.0494 -0.0279 -0.0215 -0.0008 0.0000 0.0003 -0.0048 0.264 - 94 -0.2254 4.1839 0.5386 -0.0911 0.0489 -0.0282 -0.0218 -0.0008 0.0000 0.0002 -0.0048 0.258 - 95 -0.3698 4.1268 0.6730 -0.0910 0.0481 -0.0286 -0.0220 -0.0008 0.0000 -0.0000 -0.0047 0.249 - 96 -0.5474 4.0565 0.7936 -0.0907 0.0471 -0.0290 -0.0224 -0.0008 0.0000 -0.0002 -0.0046 0.239 - 97 -0.7617 3.9717 0.9441 -0.0901 0.0458 -0.0294 -0.0227 -0.0008 0.0000 -0.0005 -0.0044 0.228 - 98 -1.0116 3.8728 1.0344 -0.0890 0.0442 -0.0298 -0.0230 -0.0009 0.0000 -0.0008 -0.0043 0.217 - 99 -1.2891 3.7630 1.1046 -0.0869 0.0425 -0.0299 -0.0231 -0.0009 0.0000 -0.0010 -0.0041 0.206 - 100 -1.5912 3.6435 1.1542 -0.0837 0.0407 -0.0298 -0.0230 -0.0009 0.0000 -0.0013 -0.0038 0.195 - 101 -1.9146 3.5155 1.1831 -0.0789 0.0389 -0.0291 -0.0224 -0.0009 0.0000 -0.0015 -0.0035 0.184 - 102 -2.2558 3.3805 1.1921 -0.0724 0.0373 -0.0278 -0.0214 -0.0008 0.0000 -0.0017 -0.0032 0.172 - 103 -2.6109 3.2400 1.1821 -0.0641 0.0357 -0.0256 -0.0198 -0.0008 0.0000 -0.0018 -0.0027 0.159 - 104 -2.9762 3.0955 1.1548 -0.0540 0.0342 -0.0226 -0.0174 -0.0007 0.0000 -0.0018 -0.0022 0.144 - 105 -3.3476 2.9485 1.1122 -0.0424 0.0330 -0.0186 -0.0144 -0.0006 0.0000 -0.0018 -0.0015 0.122 - 106 -3.7210 2.8008 1.0564 -0.0298 0.0319 -0.0138 -0.0106 -0.0004 0.0000 -0.0017 -0.0008 0.086 - 107 -4.0924 2.6538 0.9900 -0.0168 0.0311 -0.0082 -0.0063 -0.0002 0.0000 -0.0016 -0.0000 0.001 - 108 -4.4577 2.5093 0.9155 -0.0040 0.0305 -0.0020 -0.0016 -0.0001 0.0000 -0.0013 0.0008 -0.595 - 109 -4.8128 2.3687 0.8353 0.0081 0.0301 0.0044 0.0034 0.0001 0.0000 -0.0010 0.0016 0.545 - 110 -5.1540 2.2338 0.7518 0.0187 0.0299 0.0108 0.0084 0.0003 0.0000 -0.0006 0.0023 0.321 - 111 -5.4774 2.1058 0.6671 0.0275 0.0299 0.0169 0.0130 0.0004 0.0000 -0.0001 0.0029 0.258 - 112 -5.7795 1.9862 0.5830 0.0340 0.0300 0.0222 0.0171 0.0006 0.0000 0.0005 0.0033 0.224 - 113 -6.0570 1.8764 0.5012 0.0383 0.0301 0.0264 0.0204 0.0006 0.0000 0.0011 0.0034 0.198 - 114 -6.3069 1.7776 0.4225 0.0401 0.0303 0.0292 0.0225 0.0007 0.0000 0.0017 0.0034 0.175 - 115 -6.5264 1.6907 0.3478 0.0396 0.0305 0.0304 0.0234 0.0007 0.0000 0.0022 0.0031 0.154 - 116 -6.7314 1.6096 0.3326 0.0369 0.0306 0.0297 0.0229 0.0006 0.0000 0.0027 0.0026 0.132 - 117 -6.9144 1.5372 0.2507 0.0315 0.0308 0.0266 0.0205 0.0005 0.0000 0.0029 0.0019 0.109 - 118 -7.0535 1.4822 0.1746 0.0240 0.0309 0.0210 0.0162 0.0004 0.0000 0.0026 0.0012 0.088 - 119 -7.1471 1.4451 0.1029 0.0150 0.0310 0.0135 0.0104 0.0002 0.0000 0.0019 0.0007 0.072 - 120 -7.1941 1.4265 0.0340 0.0051 0.0310 0.0047 0.0036 0.0000 0.0000 0.0007 0.0002 0.063 + 91 -0.0047 4.2713 0.0803 -0.0951 0.0500 -0.0289 -0.0223 0.0011 0.0000 0.0005 -0.0052 0.273 + 92 -0.0418 4.2566 0.2392 -0.0978 0.0499 -0.0298 -0.0230 -0.0007 0.0000 0.0005 -0.0053 0.271 + 93 -0.1156 4.2274 0.3930 -0.0980 0.0495 -0.0300 -0.0232 -0.0008 0.0000 0.0004 -0.0053 0.267 + 94 -0.2254 4.1839 0.5386 -0.0980 0.0490 -0.0304 -0.0234 -0.0008 0.0000 0.0003 -0.0052 0.261 + 95 -0.3698 4.1268 0.6730 -0.0979 0.0482 -0.0308 -0.0237 -0.0009 0.0000 0.0001 -0.0051 0.253 + 96 -0.5474 4.0565 0.7936 -0.0977 0.0472 -0.0312 -0.0241 -0.0009 0.0000 -0.0002 -0.0050 0.243 + 97 -0.7617 3.9717 0.9441 -0.0970 0.0459 -0.0317 -0.0244 -0.0009 0.0000 -0.0004 -0.0048 0.232 + 98 -1.0116 3.8728 1.0344 -0.0958 0.0443 -0.0321 -0.0247 -0.0009 0.0000 -0.0007 -0.0047 0.221 + 99 -1.2891 3.7630 1.1046 -0.0937 0.0426 -0.0323 -0.0249 -0.0010 0.0000 -0.0010 -0.0045 0.210 + 100 -1.5912 3.6435 1.1542 -0.0904 0.0408 -0.0321 -0.0248 -0.0010 0.0000 -0.0013 -0.0042 0.199 + 101 -1.9146 3.5155 1.1831 -0.0855 0.0391 -0.0315 -0.0243 -0.0010 0.0000 -0.0015 -0.0039 0.189 + 102 -2.2558 3.3805 1.1921 -0.0788 0.0374 -0.0302 -0.0233 -0.0009 0.0000 -0.0017 -0.0036 0.178 + 103 -2.6109 3.2400 1.1821 -0.0702 0.0358 -0.0281 -0.0216 -0.0009 0.0000 -0.0018 -0.0031 0.166 + 104 -2.9762 3.0955 1.1548 -0.0597 0.0344 -0.0250 -0.0193 -0.0008 0.0000 -0.0019 -0.0025 0.153 + 105 -3.3476 2.9485 1.1122 -0.0478 0.0331 -0.0210 -0.0162 -0.0006 0.0000 -0.0019 -0.0019 0.134 + 106 -3.7210 2.8008 1.0564 -0.0347 0.0320 -0.0161 -0.0124 -0.0005 0.0000 -0.0018 -0.0011 0.106 + 107 -4.0924 2.6538 0.9900 -0.0212 0.0312 -0.0104 -0.0080 -0.0003 0.0000 -0.0016 -0.0003 0.048 + 108 -4.4577 2.5093 0.9155 -0.0079 0.0305 -0.0041 -0.0032 -0.0001 0.0000 -0.0014 0.0005 -0.185 + 109 -4.8128 2.3687 0.8353 0.0046 0.0301 0.0025 0.0019 0.0001 0.0000 -0.0010 0.0013 0.791 + 110 -5.1540 2.2338 0.7518 0.0157 0.0299 0.0091 0.0070 0.0002 0.0000 -0.0006 0.0020 0.341 + 111 -5.4774 2.1058 0.6671 0.0248 0.0299 0.0153 0.0118 0.0004 0.0000 -0.0001 0.0026 0.263 + 112 -5.7795 1.9862 0.5830 0.0318 0.0300 0.0208 0.0160 0.0005 0.0000 0.0004 0.0031 0.224 + 113 -6.0570 1.8764 0.5012 0.0364 0.0301 0.0251 0.0194 0.0006 0.0000 0.0010 0.0033 0.197 + 114 -6.3069 1.7776 0.4225 0.0385 0.0303 0.0281 0.0216 0.0006 0.0000 0.0016 0.0032 0.175 + 115 -6.5264 1.6907 0.3478 0.0383 0.0305 0.0293 0.0226 0.0007 0.0000 0.0022 0.0030 0.153 + 116 -6.7314 1.6096 0.3326 0.0358 0.0306 0.0288 0.0222 0.0006 0.0000 0.0027 0.0025 0.131 + 117 -6.9144 1.5372 0.2507 0.0307 0.0308 0.0259 0.0200 0.0005 0.0000 0.0028 0.0019 0.108 + 118 -7.0535 1.4822 0.1746 0.0235 0.0309 0.0205 0.0158 0.0004 0.0000 0.0026 0.0012 0.087 + 119 -7.1471 1.4451 0.1029 0.0147 0.0310 0.0132 0.0102 0.0002 0.0000 0.0018 0.0006 0.070 + 120 -7.1941 1.4265 0.0340 0.0050 0.0311 0.0046 0.0035 0.0000 0.0000 0.0007 0.0002 0.062 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,84 +198,84 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.131 - 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.114 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.105 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.082 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.068 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.062 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.080 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.098 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.108 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.102 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.115 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.137 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.154 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.168 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.183 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.194 - 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.200 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.201 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.204 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.208 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.202 - 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.190 + 121 0.0000 10.0347 0.6931 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.096 + 122 0.0000 9.8296 1.1101 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.052 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.060 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.046 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.036 + 126 0.0000 8.0598 2.2181 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.041 + 127 0.0000 7.4000 2.2957 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.076 + 128 0.0000 6.6646 2.2808 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.095 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.100 + 130 0.0000 4.9969 1.9773 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.106 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.085 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.100 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.135 + 134 0.0000 3.7615 1.5362 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.157 + 135 0.0000 3.5271 1.4499 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.172 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.175 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.189 + 138 0.0000 2.8315 1.1147 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.199 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.206 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.208 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.206 + 142 0.0000 2.0106 0.6318 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.197 + 143 0.0000 1.8390 0.5251 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.190 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.178 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.164 - 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.143 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.119 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.097 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.080 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.075 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.160 + 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.144 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.122 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.099 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.081 + 150 0.0000 1.1978 0.0252 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.077 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = -0.00067 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.01260 + CLsurf = -0.00074 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = 0.01266 CDsurf = -0.00009 Cnsurf = -0.00000 CDisurf = -0.00009 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00068 CDsurf = -0.00009 + CLsurf = -0.00075 CDsurf = -0.00009 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 -0.0341 0.0505 -0.0156 -0.0013 -0.0008 0.0000 0.0016 0.0003 1.558 - 152 -1.3090 31.2096 11.6724 -0.0331 0.0584 -0.0041 -0.0011 -0.0003 0.0000 0.0018 0.0005 1.964 - 153 -0.9350 34.0626 12.7394 -0.0227 0.0681 -0.0016 -0.0007 -0.0000 0.0000 0.0017 0.0006 - 154 -0.5610 36.1619 13.5246 -0.0137 0.0739 -0.0006 -0.0004 0.0002 0.0000 0.0017 0.0008 - 155 -0.1870 37.5332 14.0374 -0.0088 0.0770 -0.0003 -0.0002 0.0003 0.0000 0.0016 0.0012 - 156 0.1870 37.5332 14.0374 -0.0088 0.0770 -0.0003 -0.0002 0.0003 0.0000 0.0016 0.0012 - 157 0.5610 36.1619 13.5246 -0.0137 0.0739 -0.0006 -0.0004 0.0002 0.0000 0.0017 0.0008 - 158 0.9350 34.0626 12.7394 -0.0227 0.0681 -0.0016 -0.0007 -0.0000 0.0000 0.0017 0.0006 - 159 1.3090 31.2096 11.6724 -0.0331 0.0584 -0.0041 -0.0011 -0.0003 0.0000 0.0018 0.0005 1.964 - 160 1.6830 26.5957 9.9468 -0.0341 0.0505 -0.0156 -0.0013 -0.0008 0.0000 0.0016 0.0003 1.558 + 151 -1.6830 26.5957 9.9468 -0.0361 0.0504 -0.0166 -0.0013 -0.0008 0.0000 0.0017 0.0003 1.501 + 152 -1.3090 31.2096 11.6724 -0.0357 0.0583 -0.0044 -0.0011 -0.0003 0.0000 0.0018 0.0005 1.861 + 153 -0.9350 34.0626 12.7394 -0.0252 0.0682 -0.0018 -0.0007 -0.0000 0.0000 0.0018 0.0007 + 154 -0.5610 36.1619 13.5246 -0.0161 0.0741 -0.0008 -0.0005 0.0002 0.0000 0.0017 0.0008 + 155 -0.1870 37.5332 14.0374 -0.0111 0.0772 -0.0004 -0.0003 0.0003 0.0000 0.0016 0.0012 + 156 0.1870 37.5332 14.0374 -0.0111 0.0772 -0.0004 -0.0003 0.0003 0.0000 0.0016 0.0012 + 157 0.5610 36.1619 13.5246 -0.0161 0.0741 -0.0008 -0.0005 0.0002 0.0000 0.0017 0.0008 + 158 0.9350 34.0626 12.7394 -0.0252 0.0682 -0.0018 -0.0007 -0.0000 0.0000 0.0018 0.0007 + 159 1.3090 31.2096 11.6724 -0.0357 0.0583 -0.0044 -0.0011 -0.0003 0.0000 0.0018 0.0005 1.861 + 160 1.6830 26.5957 9.9468 -0.0361 0.0504 -0.0166 -0.0013 -0.0008 0.0000 0.0017 0.0003 1.501 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = -0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = -0.00000 Cnsurf = -0.00000 - CDisurf = -0.00000 CDvsurf = 0.00000 + CDsurf = 0.00000 Cnsurf = -0.00000 + CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = -0.00000 CDsurf = -0.00000 + CLsurf = -0.00000 CDsurf = 0.00000 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.301 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.548 - 163 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.545 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.544 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.552 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.589 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.587 - 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.573 - 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.563 - 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.592 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.530 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.517 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.516 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.518 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.540 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.542 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.524 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.505 + 170 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.567 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_06_04.txt b/regression/scripts/AVL/avl_files/strip_forces_case_06_04.txt index 0eaf7c6df4..e7604a317f 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_06_04.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_06_04.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.42488 Clsurf = -0.08485 - CYsurf = -0.02752 Cmsurf = -0.40039 - CDsurf = 0.01539 Cnsurf = -0.00474 - CDisurf = 0.01539 CDvsurf = 0.00000 + CLsurf = 0.42590 Clsurf = -0.08495 + CYsurf = -0.02756 Cmsurf = -0.40086 + CDsurf = 0.01544 Cnsurf = -0.00475 + CDisurf = 0.01544 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.83106 CDsurf = 0.03004 + CLsurf = 0.83305 CDsurf = 0.03014 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 5.4827 0.1520 0.8159 0.6317 0.8938 0.0000 -0.0631 -0.1964 0.350 - 2 0.1025 7.6885 1.0492 4.8209 0.1516 0.7964 0.6165 0.1472 0.0000 -0.0587 -0.1765 0.345 - 3 0.2837 7.5620 1.7073 4.7651 0.1502 0.8061 0.6241 0.0969 0.0000 -0.0568 -0.1756 0.341 - 4 0.5530 7.3741 2.3052 4.7394 0.1474 0.8236 0.6376 0.0860 0.0000 -0.0536 -0.1755 0.334 - 5 0.9075 7.1267 2.8223 4.7046 0.1422 0.8469 0.6556 0.0800 0.0000 -0.0496 -0.1759 0.326 - 6 1.3432 6.8226 3.2414 4.6484 0.1326 0.8755 0.6778 0.0702 0.0000 -0.0456 -0.1770 0.317 - 7 1.8554 6.4651 3.5491 4.5713 0.1155 0.9097 0.7043 0.0629 0.0000 -0.0420 -0.1794 0.310 - 8 2.4386 6.0582 3.7368 4.4582 0.0980 0.9479 0.7338 0.0561 0.0000 -0.0395 -0.1832 0.304 - 9 3.0862 5.6062 3.8005 4.3056 0.0862 0.9911 0.7673 0.0420 0.0000 -0.0384 -0.1889 0.300 - 10 3.7613 5.1351 3.4440 4.1409 0.0751 1.0414 0.8062 0.0378 0.0000 -0.0386 -0.1969 0.298 - 11 4.4532 4.6522 3.3149 3.9417 0.0625 1.0961 0.8485 0.0225 0.0000 -0.0404 -0.2068 0.298 - 12 5.1831 4.1429 3.0930 3.7288 0.0430 1.1663 0.9028 0.0077 0.0000 -0.0421 -0.2190 0.297 - 13 6.0123 3.7903 3.4706 3.5097 0.0295 1.1390 0.9294 0.0011 0.0000 -0.0374 -0.2415 0.290 - 14 6.9353 3.6075 3.3775 3.3386 0.0302 1.1382 0.9288 0.0020 0.0000 -0.0354 -0.2396 0.288 - 15 7.8737 3.4215 3.2389 3.1815 0.0288 1.1438 0.9333 0.0009 0.0000 -0.0338 -0.2392 0.286 - 16 8.8172 3.2345 3.0619 3.0285 0.0280 1.1519 0.9399 -0.0008 0.0000 -0.0326 -0.2396 0.285 - 17 9.7556 3.0486 2.8543 2.8763 0.0284 1.1609 0.9473 -0.0025 0.0000 -0.0315 -0.2402 0.283 - 18 10.6786 2.8657 2.6240 2.7257 0.0298 1.1705 0.9551 -0.0042 0.0000 -0.0303 -0.2409 0.282 - 19 11.5760 2.6879 2.3787 2.5725 0.0321 1.1780 0.9613 -0.0061 0.0000 -0.0289 -0.2409 0.280 - 20 12.4328 2.5181 2.1010 2.4172 0.0353 1.1817 0.9643 -0.0080 0.0000 -0.0268 -0.2398 0.278 - 21 13.2400 2.3582 1.8520 2.2575 0.0396 1.1787 0.9618 -0.0098 0.0000 -0.0239 -0.2366 0.275 - 22 13.9941 2.2087 1.6074 2.0891 0.0450 1.1648 0.9505 -0.0117 0.0000 -0.0195 -0.2301 0.270 - 23 14.6868 2.0715 1.3716 1.9073 0.0513 1.1341 0.9255 -0.0136 0.0000 -0.0133 -0.2190 0.264 - 24 15.3105 1.9479 1.1479 1.7071 0.0582 1.0797 0.8811 -0.0153 0.0000 -0.0060 -0.2025 0.257 - 25 15.8583 1.8393 0.9381 1.4832 0.0652 0.9936 0.8108 -0.0156 0.0000 -0.0005 -0.1819 0.251 - 26 16.3244 1.7470 0.7427 1.2343 0.0727 0.8703 0.7101 -0.0103 0.0000 -0.0038 -0.1624 0.255 - 27 16.6722 1.4928 0.4131 0.9716 0.0800 2.2123 0.6576 -0.0486 0.0000 -0.0067 -0.0829 0.260 - 28 16.9098 1.1466 0.2292 0.7096 0.0885 2.1139 0.6284 -0.0818 0.0000 0.0238 -0.0649 0.212 - 29 17.0696 0.9138 0.1104 0.4329 0.0940 1.6322 0.4852 -0.1088 0.0000 0.0485 -0.0358 0.150 - 30 17.1499 0.7967 0.0322 0.1455 0.0964 0.6404 0.1904 -0.0792 0.0000 0.0290 -0.0091 0.098 + 1 0.0114 7.7520 0.3539 5.5124 0.1515 0.8204 0.6351 0.8988 0.0000 -0.0654 -0.1990 0.353 + 2 0.1025 7.6885 1.0491 4.8414 0.1511 0.7998 0.6192 0.1477 0.0000 -0.0603 -0.1783 0.347 + 3 0.2837 7.5620 1.7073 4.7849 0.1500 0.8095 0.6267 0.0966 0.0000 -0.0584 -0.1774 0.343 + 4 0.5530 7.3741 2.3052 4.7586 0.1476 0.8272 0.6404 0.0841 0.0000 -0.0552 -0.1774 0.336 + 5 0.9075 7.1267 2.8223 4.7255 0.1427 0.8508 0.6587 0.0791 0.0000 -0.0513 -0.1779 0.328 + 6 1.3432 6.8226 3.2414 4.6740 0.1333 0.8800 0.6812 0.0738 0.0000 -0.0472 -0.1791 0.319 + 7 1.8554 6.4651 3.5491 4.5929 0.1163 0.9139 0.7075 0.0642 0.0000 -0.0437 -0.1814 0.312 + 8 2.4386 6.0582 3.7368 4.4786 0.0991 0.9523 0.7372 0.0555 0.0000 -0.0412 -0.1853 0.306 + 9 3.0862 5.6062 3.8005 4.3296 0.0880 0.9964 0.7713 0.0444 0.0000 -0.0400 -0.1911 0.302 + 10 3.7613 5.1351 3.4440 4.1780 0.0766 1.0512 0.8138 0.0338 0.0000 -0.0390 -0.1987 0.298 + 11 4.4532 4.6522 3.3149 3.9447 0.0625 1.0968 0.8490 0.0244 0.0000 -0.0389 -0.2057 0.296 + 12 5.1831 4.1429 3.0930 3.7334 0.0418 1.1678 0.9040 0.0069 0.0000 -0.0406 -0.2181 0.295 + 13 6.0123 3.7903 3.4706 3.5158 0.0289 1.1409 0.9310 0.0013 0.0000 -0.0354 -0.2400 0.288 + 14 6.9353 3.6075 3.3775 3.3431 0.0298 1.1398 0.9301 0.0019 0.0000 -0.0331 -0.2379 0.286 + 15 7.8737 3.4215 3.2389 3.1844 0.0286 1.1448 0.9342 0.0010 0.0000 -0.0314 -0.2372 0.284 + 16 8.8172 3.2345 3.0619 3.0309 0.0278 1.1528 0.9407 -0.0008 0.0000 -0.0300 -0.2375 0.282 + 17 9.7556 3.0486 2.8543 2.8787 0.0283 1.1619 0.9481 -0.0025 0.0000 -0.0289 -0.2381 0.280 + 18 10.6786 2.8657 2.6239 2.7275 0.0298 1.1713 0.9558 -0.0043 0.0000 -0.0277 -0.2387 0.279 + 19 11.5760 2.6879 2.3787 2.5741 0.0321 1.1787 0.9619 -0.0062 0.0000 -0.0262 -0.2387 0.277 + 20 12.4328 2.5181 2.1010 2.4185 0.0353 1.1824 0.9648 -0.0081 0.0000 -0.0242 -0.2375 0.275 + 21 13.2400 2.3582 1.8520 2.2585 0.0395 1.1792 0.9622 -0.0099 0.0000 -0.0212 -0.2343 0.272 + 22 13.9941 2.2087 1.6074 2.0899 0.0449 1.1652 0.9508 -0.0119 0.0000 -0.0168 -0.2278 0.268 + 23 14.6868 2.0715 1.3716 1.9076 0.0513 1.1343 0.9256 -0.0138 0.0000 -0.0106 -0.2166 0.261 + 24 15.3105 1.9479 1.1479 1.7069 0.0581 1.0796 0.8810 -0.0155 0.0000 -0.0033 -0.2001 0.254 + 25 15.8583 1.8393 0.9381 1.4827 0.0651 0.9933 0.8106 -0.0158 0.0000 0.0022 -0.1795 0.247 + 26 16.3244 1.7470 0.7427 1.2330 0.0721 0.8694 0.7094 -0.0106 0.0000 -0.0012 -0.1599 0.252 + 27 16.6722 1.4928 0.4131 0.9704 0.0794 2.2098 0.6569 -0.0492 0.0000 -0.0046 -0.0818 0.257 + 28 16.9098 1.1466 0.2292 0.7088 0.0881 2.1118 0.6278 -0.0822 0.0000 0.0256 -0.0640 0.209 + 29 17.0696 0.9138 0.1104 0.4325 0.0938 1.6309 0.4848 -0.1094 0.0000 0.0497 -0.0352 0.148 + 30 17.1499 0.7967 0.0322 0.1455 0.0971 0.6405 0.1904 -0.0799 0.0000 0.0293 -0.0089 0.096 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.42488 Clsurf = 0.08485 - CYsurf = 0.02752 Cmsurf = -0.40039 - CDsurf = 0.01539 Cnsurf = 0.00474 - CDisurf = 0.01539 CDvsurf = 0.00000 + CLsurf = 0.42590 Clsurf = 0.08495 + CYsurf = 0.02756 Cmsurf = -0.40086 + CDsurf = 0.01544 Cnsurf = 0.00475 + CDisurf = 0.01544 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.83105 CDsurf = 0.03004 + CLsurf = 0.83305 CDsurf = 0.03014 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 5.4827 0.1521 0.8159 0.6317 0.8939 0.0000 -0.0631 0.1964 0.350 - 32 -0.1025 7.6885 1.0492 4.8209 0.1516 0.7964 0.6165 0.1472 0.0000 -0.0587 0.1765 0.345 - 33 -0.2837 7.5620 1.7073 4.7651 0.1502 0.8061 0.6241 0.0969 0.0000 -0.0568 0.1756 0.341 - 34 -0.5530 7.3741 2.3052 4.7394 0.1474 0.8236 0.6376 0.0860 0.0000 -0.0536 0.1755 0.334 - 35 -0.9075 7.1267 2.8223 4.7046 0.1422 0.8469 0.6556 0.0800 0.0000 -0.0496 0.1759 0.326 - 36 -1.3432 6.8226 3.2414 4.6484 0.1326 0.8755 0.6778 0.0702 0.0000 -0.0456 0.1770 0.317 - 37 -1.8554 6.4651 3.5491 4.5713 0.1155 0.9097 0.7043 0.0629 0.0000 -0.0420 0.1794 0.310 - 38 -2.4386 6.0582 3.7368 4.4582 0.0980 0.9479 0.7338 0.0561 0.0000 -0.0395 0.1832 0.304 - 39 -3.0862 5.6062 3.8005 4.3056 0.0862 0.9911 0.7673 0.0420 0.0000 -0.0384 0.1889 0.300 - 40 -3.7613 5.1351 3.4440 4.1409 0.0751 1.0414 0.8062 0.0378 0.0000 -0.0386 0.1969 0.298 - 41 -4.4532 4.6522 3.3149 3.9416 0.0625 1.0961 0.8485 0.0225 0.0000 -0.0404 0.2068 0.298 - 42 -5.1831 4.1429 3.0930 3.7288 0.0430 1.1663 0.9028 0.0077 0.0000 -0.0421 0.2190 0.297 - 43 -6.0123 3.7903 3.4706 3.5097 0.0295 1.1389 0.9294 0.0011 0.0000 -0.0374 0.2415 0.290 - 44 -6.9353 3.6075 3.3775 3.3386 0.0302 1.1382 0.9288 0.0020 0.0000 -0.0354 0.2396 0.288 - 45 -7.8737 3.4215 3.2389 3.1815 0.0288 1.1438 0.9333 0.0009 0.0000 -0.0338 0.2392 0.286 - 46 -8.8172 3.2345 3.0619 3.0285 0.0280 1.1519 0.9399 -0.0008 0.0000 -0.0326 0.2396 0.285 - 47 -9.7556 3.0486 2.8543 2.8763 0.0284 1.1609 0.9473 -0.0025 0.0000 -0.0315 0.2402 0.283 - 48 -10.6786 2.8657 2.6240 2.7257 0.0298 1.1705 0.9551 -0.0042 0.0000 -0.0303 0.2409 0.282 - 49 -11.5760 2.6879 2.3787 2.5725 0.0321 1.1780 0.9613 -0.0061 0.0000 -0.0289 0.2409 0.280 - 50 -12.4328 2.5181 2.1010 2.4172 0.0353 1.1817 0.9643 -0.0080 0.0000 -0.0268 0.2398 0.278 - 51 -13.2400 2.3582 1.8520 2.2575 0.0396 1.1787 0.9618 -0.0098 0.0000 -0.0239 0.2366 0.275 - 52 -13.9941 2.2087 1.6074 2.0891 0.0450 1.1647 0.9504 -0.0117 0.0000 -0.0195 0.2301 0.270 - 53 -14.6868 2.0715 1.3716 1.9073 0.0513 1.1341 0.9254 -0.0136 0.0000 -0.0133 0.2190 0.264 - 54 -15.3105 1.9479 1.1479 1.7071 0.0582 1.0797 0.8810 -0.0153 0.0000 -0.0060 0.2025 0.257 - 55 -15.8583 1.8393 0.9381 1.4831 0.0652 0.9936 0.8108 -0.0156 0.0000 -0.0005 0.1819 0.251 - 56 -16.3244 1.7470 0.7427 1.2343 0.0727 0.8703 0.7101 -0.0103 0.0000 -0.0038 0.1624 0.255 - 57 -16.6722 1.4928 0.4131 0.9716 0.0800 2.2123 0.6576 -0.0486 0.0000 -0.0067 0.0829 0.260 - 58 -16.9098 1.1466 0.2292 0.7095 0.0885 2.1139 0.6284 -0.0818 0.0000 0.0238 0.0649 0.212 - 59 -17.0696 0.9138 0.1104 0.4329 0.0940 1.6322 0.4852 -0.1088 0.0000 0.0485 0.0358 0.150 - 60 -17.1499 0.7967 0.0322 0.1455 0.0964 0.6404 0.1904 -0.0792 0.0000 0.0290 0.0091 0.098 + 31 -0.0114 7.7520 0.3539 5.5124 0.1515 0.8204 0.6351 0.8988 0.0000 -0.0654 0.1990 0.353 + 32 -0.1025 7.6885 1.0491 4.8414 0.1511 0.7998 0.6192 0.1477 0.0000 -0.0603 0.1783 0.347 + 33 -0.2837 7.5620 1.7073 4.7849 0.1500 0.8095 0.6267 0.0966 0.0000 -0.0584 0.1774 0.343 + 34 -0.5530 7.3741 2.3052 4.7586 0.1476 0.8272 0.6404 0.0841 0.0000 -0.0552 0.1774 0.336 + 35 -0.9075 7.1267 2.8223 4.7255 0.1427 0.8508 0.6587 0.0791 0.0000 -0.0513 0.1779 0.328 + 36 -1.3432 6.8226 3.2414 4.6740 0.1333 0.8800 0.6812 0.0738 0.0000 -0.0472 0.1791 0.319 + 37 -1.8554 6.4651 3.5491 4.5929 0.1163 0.9139 0.7075 0.0642 0.0000 -0.0437 0.1814 0.312 + 38 -2.4386 6.0582 3.7368 4.4786 0.0991 0.9523 0.7372 0.0555 0.0000 -0.0412 0.1853 0.306 + 39 -3.0862 5.6062 3.8005 4.3296 0.0880 0.9964 0.7713 0.0444 0.0000 -0.0400 0.1911 0.302 + 40 -3.7613 5.1351 3.4440 4.1780 0.0766 1.0512 0.8138 0.0338 0.0000 -0.0390 0.1987 0.298 + 41 -4.4532 4.6522 3.3149 3.9447 0.0625 1.0968 0.8490 0.0244 0.0000 -0.0389 0.2057 0.296 + 42 -5.1831 4.1429 3.0930 3.7334 0.0418 1.1678 0.9040 0.0069 0.0000 -0.0406 0.2181 0.295 + 43 -6.0123 3.7903 3.4706 3.5158 0.0289 1.1409 0.9310 0.0013 0.0000 -0.0354 0.2400 0.288 + 44 -6.9353 3.6075 3.3775 3.3431 0.0298 1.1398 0.9301 0.0019 0.0000 -0.0331 0.2378 0.286 + 45 -7.8737 3.4215 3.2389 3.1844 0.0286 1.1448 0.9342 0.0010 0.0000 -0.0314 0.2372 0.284 + 46 -8.8172 3.2345 3.0619 3.0309 0.0278 1.1528 0.9407 -0.0008 0.0000 -0.0300 0.2375 0.282 + 47 -9.7556 3.0486 2.8543 2.8787 0.0283 1.1619 0.9481 -0.0025 0.0000 -0.0289 0.2381 0.280 + 48 -10.6786 2.8657 2.6239 2.7275 0.0298 1.1713 0.9558 -0.0043 0.0000 -0.0277 0.2387 0.279 + 49 -11.5760 2.6879 2.3787 2.5741 0.0321 1.1787 0.9619 -0.0062 0.0000 -0.0262 0.2387 0.277 + 50 -12.4328 2.5181 2.1010 2.4185 0.0353 1.1824 0.9648 -0.0081 0.0000 -0.0242 0.2375 0.275 + 51 -13.2400 2.3582 1.8520 2.2585 0.0395 1.1792 0.9622 -0.0099 0.0000 -0.0212 0.2343 0.272 + 52 -13.9941 2.2087 1.6074 2.0899 0.0449 1.1652 0.9508 -0.0119 0.0000 -0.0168 0.2278 0.268 + 53 -14.6868 2.0715 1.3716 1.9076 0.0513 1.1343 0.9256 -0.0138 0.0000 -0.0106 0.2166 0.261 + 54 -15.3105 1.9479 1.1479 1.7069 0.0581 1.0796 0.8810 -0.0155 0.0000 -0.0033 0.2001 0.254 + 55 -15.8583 1.8393 0.9381 1.4827 0.0651 0.9933 0.8106 -0.0158 0.0000 0.0022 0.1795 0.247 + 56 -16.3244 1.7470 0.7427 1.2330 0.0721 0.8694 0.7094 -0.0106 0.0000 -0.0012 0.1599 0.252 + 57 -16.6722 1.4928 0.4131 0.9704 0.0794 2.2098 0.6569 -0.0492 0.0000 -0.0046 0.0818 0.257 + 58 -16.9098 1.1466 0.2292 0.7088 0.0881 2.1118 0.6278 -0.0822 0.0000 0.0256 0.0640 0.209 + 59 -17.0696 0.9138 0.1104 0.4325 0.0938 1.6309 0.4848 -0.1094 0.0000 0.0497 0.0352 0.148 + 60 -17.1499 0.7967 0.0322 0.1455 0.0971 0.6405 0.1904 -0.0799 0.0000 0.0293 0.0089 0.096 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02620 Clsurf = -0.00281 - CYsurf = -0.00432 Cmsurf = -0.12835 - CDsurf = 0.00177 Cnsurf = 0.00249 - CDisurf = 0.00177 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02594 Clsurf = -0.00279 + CYsurf = -0.00428 Cmsurf = -0.12710 + CDsurf = 0.00176 Cnsurf = 0.00247 + CDisurf = 0.00176 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.15984 CDsurf = 0.01067 + CLsurf = 0.15825 CDsurf = 0.01058 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 0.5835 0.1047 0.1729 0.1324 0.0542 0.0000 -0.0126 -0.0400 0.345 - 62 0.0418 4.2566 0.2392 0.5189 0.1049 0.1582 0.1212 0.0134 0.0000 -0.0116 -0.0361 0.346 - 63 0.1156 4.2274 0.3930 0.5139 0.1048 0.1581 0.1211 0.0105 0.0000 -0.0113 -0.0357 0.343 - 64 0.2254 4.1839 0.5386 0.5127 0.1043 0.1595 0.1221 0.0100 0.0000 -0.0108 -0.0355 0.338 - 65 0.3698 4.1268 0.6730 0.5119 0.1032 0.1614 0.1236 0.0099 0.0000 -0.0100 -0.0352 0.331 - 66 0.5474 4.0565 0.7936 0.5113 0.1014 0.1640 0.1257 0.0099 0.0000 -0.0091 -0.0349 0.323 - 67 0.7617 3.9717 0.9441 0.5103 0.0988 0.1672 0.1281 0.0099 0.0000 -0.0082 -0.0346 0.314 - 68 1.0116 3.8728 1.0344 0.5086 0.0953 0.1710 0.1309 0.0100 0.0000 -0.0073 -0.0345 0.306 - 69 1.2891 3.7630 1.1046 0.5066 0.0911 0.1753 0.1343 0.0101 0.0000 -0.0065 -0.0345 0.298 - 70 1.5912 3.6435 1.1542 0.5047 0.0864 0.1804 0.1381 0.0102 0.0000 -0.0057 -0.0347 0.291 - 71 1.9146 3.5155 1.1831 0.5025 0.0818 0.1861 0.1426 0.0104 0.0000 -0.0050 -0.0351 0.285 - 72 2.2558 3.3805 1.1921 0.5008 0.0777 0.1929 0.1478 0.0106 0.0000 -0.0044 -0.0357 0.280 - 73 2.6109 3.2400 1.1821 0.4994 0.0744 0.2007 0.1538 0.0108 0.0000 -0.0038 -0.0365 0.275 - 74 2.9762 3.0955 1.1548 0.4982 0.0718 0.2096 0.1606 0.0111 0.0000 -0.0031 -0.0374 0.269 - 75 3.3476 2.9485 1.1122 0.4968 0.0700 0.2195 0.1681 0.0114 0.0000 -0.0024 -0.0384 0.264 - 76 3.7210 2.8008 1.0564 0.4947 0.0687 0.2302 0.1763 0.0116 0.0000 -0.0016 -0.0395 0.259 - 77 4.0924 2.6538 0.9900 0.4913 0.0680 0.2412 0.1848 0.0119 0.0000 -0.0006 -0.0405 0.253 - 78 4.4577 2.5093 0.9155 0.4856 0.0678 0.2522 0.1932 0.0120 0.0000 0.0006 -0.0413 0.247 - 79 4.8128 2.3687 0.8353 0.4767 0.0680 0.2624 0.2010 0.0120 0.0000 0.0020 -0.0418 0.240 - 80 5.1540 2.2338 0.7518 0.4641 0.0685 0.2709 0.2075 0.0119 0.0000 0.0038 -0.0417 0.232 - 81 5.4774 2.1058 0.6671 0.4470 0.0693 0.2768 0.2120 0.0117 0.0000 0.0060 -0.0409 0.222 - 82 5.7795 1.9862 0.5830 0.4246 0.0704 0.2789 0.2136 0.0111 0.0000 0.0084 -0.0392 0.211 - 83 6.0570 1.8764 0.5012 0.3967 0.0714 0.2759 0.2113 0.0104 0.0000 0.0111 -0.0364 0.197 - 84 6.3069 1.7776 0.4225 0.3635 0.0725 0.2669 0.2044 0.0094 0.0000 0.0139 -0.0326 0.182 - 85 6.5264 1.6907 0.3478 0.3250 0.0735 0.2510 0.1922 0.0080 0.0000 0.0162 -0.0279 0.165 - 86 6.7314 1.6096 0.3326 0.2793 0.0744 0.2267 0.1736 0.0064 0.0000 0.0180 -0.0225 0.147 - 87 6.9144 1.5372 0.2507 0.2245 0.0752 0.1909 0.1462 0.0045 0.0000 0.0182 -0.0163 0.126 - 88 7.0535 1.4822 0.1746 0.1641 0.0758 0.1449 0.1109 0.0023 0.0000 0.0160 -0.0105 0.106 - 89 7.1471 1.4451 0.1029 0.1000 0.0762 0.0906 0.0694 0.0005 0.0000 0.0111 -0.0057 0.090 - 90 7.1941 1.4265 0.0340 0.0336 0.0764 0.0310 0.0238 -0.0014 0.0000 0.0040 -0.0018 0.083 + 61 0.0047 4.2713 0.0803 0.5747 0.1048 0.1703 0.1305 0.0528 0.0000 -0.0124 -0.0394 0.345 + 62 0.0418 4.2566 0.2392 0.5118 0.1050 0.1561 0.1195 0.0132 0.0000 -0.0115 -0.0356 0.346 + 63 0.1156 4.2274 0.3930 0.5068 0.1049 0.1559 0.1194 0.0103 0.0000 -0.0112 -0.0353 0.344 + 64 0.2254 4.1839 0.5386 0.5058 0.1044 0.1573 0.1205 0.0098 0.0000 -0.0107 -0.0351 0.339 + 65 0.3698 4.1268 0.6730 0.5051 0.1033 0.1593 0.1220 0.0097 0.0000 -0.0099 -0.0348 0.331 + 66 0.5474 4.0565 0.7936 0.5045 0.1015 0.1618 0.1240 0.0098 0.0000 -0.0091 -0.0345 0.323 + 67 0.7617 3.9717 0.9441 0.5034 0.0989 0.1650 0.1264 0.0098 0.0000 -0.0082 -0.0342 0.315 + 68 1.0116 3.8728 1.0344 0.5017 0.0954 0.1686 0.1292 0.0099 0.0000 -0.0073 -0.0341 0.306 + 69 1.2891 3.7630 1.1046 0.4999 0.0912 0.1729 0.1325 0.0100 0.0000 -0.0064 -0.0341 0.299 + 70 1.5912 3.6435 1.1542 0.4979 0.0866 0.1779 0.1363 0.0101 0.0000 -0.0057 -0.0343 0.292 + 71 1.9146 3.5155 1.1831 0.4961 0.0820 0.1837 0.1407 0.0103 0.0000 -0.0050 -0.0347 0.286 + 72 2.2558 3.3805 1.1921 0.4945 0.0778 0.1905 0.1459 0.0105 0.0000 -0.0044 -0.0353 0.280 + 73 2.6109 3.2400 1.1821 0.4933 0.0745 0.1983 0.1519 0.0107 0.0000 -0.0038 -0.0361 0.275 + 74 2.9762 3.0955 1.1548 0.4926 0.0720 0.2073 0.1588 0.0110 0.0000 -0.0031 -0.0370 0.270 + 75 3.3476 2.9485 1.1122 0.4915 0.0701 0.2172 0.1663 0.0113 0.0000 -0.0024 -0.0381 0.265 + 76 3.7210 2.8008 1.0564 0.4898 0.0688 0.2279 0.1745 0.0116 0.0000 -0.0016 -0.0392 0.259 + 77 4.0924 2.6538 0.9900 0.4869 0.0681 0.2391 0.1831 0.0118 0.0000 -0.0006 -0.0402 0.253 + 78 4.4577 2.5093 0.9155 0.4817 0.0678 0.2502 0.1916 0.0119 0.0000 0.0006 -0.0410 0.247 + 79 4.8128 2.3687 0.8353 0.4734 0.0680 0.2605 0.1995 0.0120 0.0000 0.0020 -0.0415 0.240 + 80 5.1540 2.2338 0.7518 0.4612 0.0685 0.2692 0.2062 0.0119 0.0000 0.0038 -0.0415 0.232 + 81 5.4774 2.1058 0.6671 0.4444 0.0694 0.2752 0.2108 0.0116 0.0000 0.0059 -0.0407 0.222 + 82 5.7795 1.9862 0.5830 0.4223 0.0704 0.2774 0.2124 0.0111 0.0000 0.0084 -0.0390 0.211 + 83 6.0570 1.8764 0.5012 0.3949 0.0715 0.2746 0.2103 0.0103 0.0000 0.0111 -0.0362 0.197 + 84 6.3069 1.7776 0.4225 0.3619 0.0725 0.2658 0.2036 0.0093 0.0000 0.0138 -0.0325 0.182 + 85 6.5264 1.6907 0.3478 0.3237 0.0735 0.2500 0.1915 0.0080 0.0000 0.0162 -0.0278 0.165 + 86 6.7314 1.6096 0.3326 0.2783 0.0744 0.2259 0.1730 0.0064 0.0000 0.0179 -0.0224 0.146 + 87 6.9144 1.5372 0.2507 0.2237 0.0752 0.1902 0.1457 0.0045 0.0000 0.0181 -0.0163 0.125 + 88 7.0535 1.4822 0.1746 0.1636 0.0758 0.1444 0.1106 0.0023 0.0000 0.0160 -0.0105 0.106 + 89 7.1471 1.4451 0.1029 0.0997 0.0762 0.0904 0.0692 0.0005 0.0000 0.0111 -0.0056 0.090 + 90 7.1941 1.4265 0.0340 0.0335 0.0764 0.0309 0.0237 -0.0013 0.0000 0.0040 -0.0018 0.083 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.02620 Clsurf = 0.00281 - CYsurf = 0.00432 Cmsurf = -0.12835 - CDsurf = 0.00177 Cnsurf = -0.00249 - CDisurf = 0.00177 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.02594 Clsurf = 0.00279 + CYsurf = 0.00428 Cmsurf = -0.12710 + CDsurf = 0.00176 Cnsurf = -0.00247 + CDisurf = 0.00176 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.15984 CDsurf = 0.01067 + CLsurf = 0.15825 CDsurf = 0.01058 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 0.5835 0.1047 0.1729 0.1324 0.0542 0.0000 -0.0126 0.0400 0.345 - 92 -0.0418 4.2566 0.2392 0.5189 0.1049 0.1582 0.1212 0.0134 0.0000 -0.0116 0.0361 0.346 - 93 -0.1156 4.2274 0.3930 0.5139 0.1048 0.1581 0.1211 0.0105 0.0000 -0.0113 0.0357 0.343 - 94 -0.2254 4.1839 0.5386 0.5127 0.1043 0.1595 0.1221 0.0100 0.0000 -0.0108 0.0355 0.338 - 95 -0.3698 4.1268 0.6730 0.5119 0.1032 0.1614 0.1236 0.0099 0.0000 -0.0100 0.0352 0.331 - 96 -0.5474 4.0565 0.7936 0.5113 0.1014 0.1640 0.1257 0.0099 0.0000 -0.0091 0.0349 0.323 - 97 -0.7617 3.9717 0.9441 0.5103 0.0988 0.1672 0.1281 0.0099 0.0000 -0.0082 0.0346 0.314 - 98 -1.0116 3.8728 1.0344 0.5086 0.0953 0.1710 0.1309 0.0100 0.0000 -0.0073 0.0345 0.306 - 99 -1.2891 3.7630 1.1046 0.5066 0.0911 0.1753 0.1343 0.0101 0.0000 -0.0065 0.0345 0.298 - 100 -1.5912 3.6435 1.1542 0.5047 0.0864 0.1804 0.1381 0.0102 0.0000 -0.0057 0.0347 0.291 - 101 -1.9146 3.5155 1.1831 0.5025 0.0818 0.1861 0.1426 0.0104 0.0000 -0.0050 0.0351 0.285 - 102 -2.2558 3.3805 1.1921 0.5008 0.0777 0.1929 0.1478 0.0106 0.0000 -0.0044 0.0357 0.280 - 103 -2.6109 3.2400 1.1821 0.4993 0.0744 0.2007 0.1538 0.0108 0.0000 -0.0038 0.0365 0.275 - 104 -2.9762 3.0955 1.1548 0.4981 0.0718 0.2096 0.1606 0.0111 0.0000 -0.0031 0.0374 0.269 - 105 -3.3476 2.9485 1.1122 0.4967 0.0700 0.2195 0.1681 0.0114 0.0000 -0.0024 0.0384 0.264 - 106 -3.7210 2.8008 1.0564 0.4947 0.0687 0.2302 0.1763 0.0116 0.0000 -0.0016 0.0395 0.259 - 107 -4.0924 2.6538 0.9900 0.4913 0.0680 0.2412 0.1848 0.0119 0.0000 -0.0006 0.0405 0.253 - 108 -4.4577 2.5093 0.9155 0.4856 0.0678 0.2522 0.1932 0.0120 0.0000 0.0006 0.0413 0.247 - 109 -4.8128 2.3687 0.8353 0.4767 0.0680 0.2624 0.2010 0.0120 0.0000 0.0020 0.0418 0.240 - 110 -5.1540 2.2338 0.7518 0.4641 0.0685 0.2709 0.2075 0.0119 0.0000 0.0038 0.0417 0.232 - 111 -5.4774 2.1058 0.6671 0.4470 0.0693 0.2768 0.2120 0.0117 0.0000 0.0060 0.0409 0.222 - 112 -5.7795 1.9862 0.5830 0.4246 0.0704 0.2789 0.2136 0.0111 0.0000 0.0084 0.0392 0.211 - 113 -6.0570 1.8764 0.5012 0.3967 0.0714 0.2759 0.2113 0.0104 0.0000 0.0111 0.0364 0.197 - 114 -6.3069 1.7776 0.4225 0.3635 0.0725 0.2669 0.2044 0.0094 0.0000 0.0139 0.0326 0.182 - 115 -6.5264 1.6907 0.3478 0.3250 0.0735 0.2510 0.1922 0.0080 0.0000 0.0162 0.0279 0.165 - 116 -6.7314 1.6096 0.3326 0.2793 0.0744 0.2267 0.1736 0.0064 0.0000 0.0180 0.0225 0.147 - 117 -6.9144 1.5372 0.2507 0.2244 0.0752 0.1909 0.1462 0.0045 0.0000 0.0182 0.0163 0.126 - 118 -7.0535 1.4822 0.1746 0.1641 0.0758 0.1449 0.1109 0.0023 0.0000 0.0160 0.0105 0.106 - 119 -7.1471 1.4451 0.1029 0.1000 0.0762 0.0906 0.0694 0.0005 0.0000 0.0111 0.0057 0.090 - 120 -7.1941 1.4265 0.0340 0.0336 0.0764 0.0310 0.0238 -0.0014 0.0000 0.0040 0.0018 0.083 + 91 -0.0047 4.2713 0.0803 0.5747 0.1048 0.1703 0.1305 0.0528 0.0000 -0.0124 0.0394 0.345 + 92 -0.0418 4.2566 0.2392 0.5118 0.1050 0.1561 0.1195 0.0132 0.0000 -0.0115 0.0356 0.346 + 93 -0.1156 4.2274 0.3930 0.5068 0.1049 0.1559 0.1194 0.0103 0.0000 -0.0112 0.0353 0.344 + 94 -0.2254 4.1839 0.5386 0.5058 0.1044 0.1573 0.1205 0.0098 0.0000 -0.0107 0.0351 0.339 + 95 -0.3698 4.1268 0.6730 0.5051 0.1033 0.1593 0.1220 0.0097 0.0000 -0.0099 0.0348 0.331 + 96 -0.5474 4.0565 0.7936 0.5045 0.1015 0.1618 0.1240 0.0098 0.0000 -0.0091 0.0345 0.323 + 97 -0.7617 3.9717 0.9441 0.5034 0.0989 0.1650 0.1264 0.0098 0.0000 -0.0082 0.0342 0.315 + 98 -1.0116 3.8728 1.0344 0.5017 0.0954 0.1686 0.1292 0.0099 0.0000 -0.0073 0.0341 0.306 + 99 -1.2891 3.7630 1.1046 0.4999 0.0912 0.1729 0.1325 0.0100 0.0000 -0.0064 0.0341 0.299 + 100 -1.5912 3.6435 1.1542 0.4979 0.0866 0.1779 0.1363 0.0101 0.0000 -0.0057 0.0343 0.292 + 101 -1.9146 3.5155 1.1831 0.4961 0.0820 0.1837 0.1407 0.0103 0.0000 -0.0050 0.0347 0.286 + 102 -2.2558 3.3805 1.1921 0.4945 0.0778 0.1905 0.1459 0.0105 0.0000 -0.0044 0.0353 0.280 + 103 -2.6109 3.2400 1.1821 0.4933 0.0745 0.1983 0.1519 0.0107 0.0000 -0.0038 0.0361 0.275 + 104 -2.9762 3.0955 1.1548 0.4926 0.0720 0.2073 0.1588 0.0110 0.0000 -0.0031 0.0370 0.270 + 105 -3.3476 2.9485 1.1122 0.4915 0.0701 0.2172 0.1663 0.0113 0.0000 -0.0024 0.0381 0.265 + 106 -3.7210 2.8008 1.0564 0.4898 0.0688 0.2279 0.1745 0.0116 0.0000 -0.0016 0.0392 0.259 + 107 -4.0924 2.6538 0.9900 0.4869 0.0681 0.2391 0.1831 0.0118 0.0000 -0.0006 0.0402 0.253 + 108 -4.4577 2.5093 0.9155 0.4817 0.0678 0.2502 0.1916 0.0119 0.0000 0.0006 0.0410 0.247 + 109 -4.8128 2.3687 0.8353 0.4734 0.0680 0.2605 0.1995 0.0120 0.0000 0.0020 0.0415 0.240 + 110 -5.1540 2.2338 0.7518 0.4612 0.0685 0.2692 0.2062 0.0119 0.0000 0.0038 0.0415 0.232 + 111 -5.4774 2.1058 0.6671 0.4444 0.0694 0.2752 0.2108 0.0116 0.0000 0.0059 0.0407 0.222 + 112 -5.7795 1.9862 0.5830 0.4223 0.0704 0.2774 0.2124 0.0111 0.0000 0.0084 0.0390 0.211 + 113 -6.0570 1.8764 0.5012 0.3948 0.0715 0.2746 0.2103 0.0103 0.0000 0.0111 0.0362 0.197 + 114 -6.3069 1.7776 0.4225 0.3619 0.0725 0.2658 0.2036 0.0093 0.0000 0.0138 0.0325 0.182 + 115 -6.5264 1.6907 0.3478 0.3237 0.0735 0.2500 0.1915 0.0080 0.0000 0.0162 0.0278 0.165 + 116 -6.7314 1.6096 0.3326 0.2783 0.0744 0.2259 0.1730 0.0064 0.0000 0.0179 0.0224 0.146 + 117 -6.9144 1.5372 0.2507 0.2237 0.0752 0.1902 0.1457 0.0045 0.0000 0.0181 0.0163 0.125 + 118 -7.0535 1.4822 0.1746 0.1636 0.0758 0.1444 0.1106 0.0023 0.0000 0.0160 0.0105 0.106 + 119 -7.1471 1.4451 0.1029 0.0997 0.0762 0.0904 0.0692 0.0005 0.0000 0.0111 0.0056 0.090 + 120 -7.1941 1.4265 0.0340 0.0335 0.0764 0.0309 0.0237 -0.0013 0.0000 0.0040 0.0018 0.083 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,68 +198,68 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.417 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.424 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.434 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.443 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.449 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.450 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.448 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.434 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.407 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.369 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.329 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.313 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.301 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.290 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.279 - 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.271 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.263 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.447 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.445 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.461 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.470 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.476 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.471 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.467 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.448 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.419 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.375 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.331 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.314 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.307 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.296 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.285 + 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.270 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.261 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.254 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.244 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.238 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.221 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.249 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.231 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.219 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.207 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.192 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.174 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.173 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.153 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.129 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.107 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.090 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.083 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.132 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.109 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.092 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.085 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.00581 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.04155 + CLsurf = 0.00574 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = 0.04162 CDsurf = -0.00016 Cnsurf = -0.00000 CDisurf = -0.00016 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.00586 CDsurf = -0.00016 + CLsurf = 0.00579 CDsurf = -0.00016 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.1231 0.1373 0.0562 0.0048 -0.0023 0.0000 0.0031 0.0003 -0.391 - 152 -1.3090 31.2096 11.6724 0.1847 0.1503 0.0229 0.0060 -0.0008 0.0000 0.0038 0.0006 -0.386 - 153 -0.9350 34.0626 12.7394 0.2059 0.1433 0.0147 0.0061 -0.0000 0.0000 0.0046 0.0010 -0.501 - 154 -0.5610 36.1619 13.5246 0.2207 0.1437 0.0102 0.0061 0.0005 0.0000 0.0049 0.0015 -0.551 - 155 -0.1870 37.5332 14.0374 0.2297 0.1460 0.0070 0.0060 0.0012 0.0000 0.0049 0.0024 -0.569 - 156 0.1870 37.5332 14.0374 0.2297 0.1460 0.0070 0.0060 0.0012 0.0000 0.0049 0.0024 -0.569 - 157 0.5610 36.1619 13.5246 0.2207 0.1437 0.0102 0.0061 0.0005 0.0000 0.0049 0.0015 -0.551 - 158 0.9350 34.0626 12.7394 0.2059 0.1433 0.0147 0.0061 -0.0000 0.0000 0.0046 0.0010 -0.501 - 159 1.3090 31.2096 11.6724 0.1847 0.1503 0.0229 0.0060 -0.0008 0.0000 0.0038 0.0006 -0.386 - 160 1.6830 26.5957 9.9468 0.1231 0.1373 0.0562 0.0048 -0.0023 0.0000 0.0031 0.0003 -0.391 + 151 -1.6830 26.5957 9.9468 0.1211 0.1372 0.0553 0.0048 -0.0023 0.0000 0.0031 0.0003 -0.406 + 152 -1.3090 31.2096 11.6724 0.1821 0.1502 0.0226 0.0059 -0.0008 0.0000 0.0038 0.0006 -0.399 + 153 -0.9350 34.0626 12.7394 0.2034 0.1435 0.0145 0.0060 -0.0000 0.0000 0.0046 0.0010 -0.513 + 154 -0.5610 36.1619 13.5246 0.2184 0.1439 0.0101 0.0060 0.0005 0.0000 0.0049 0.0015 -0.562 + 155 -0.1870 37.5332 14.0374 0.2275 0.1462 0.0069 0.0060 0.0012 0.0000 0.0050 0.0024 -0.579 + 156 0.1870 37.5332 14.0374 0.2275 0.1462 0.0069 0.0060 0.0012 0.0000 0.0050 0.0024 -0.579 + 157 0.5610 36.1619 13.5246 0.2184 0.1439 0.0101 0.0060 0.0005 0.0000 0.0049 0.0015 -0.562 + 158 0.9350 34.0626 12.7394 0.2034 0.1435 0.0145 0.0060 -0.0000 0.0000 0.0046 0.0010 -0.513 + 159 1.3090 31.2096 11.6724 0.1821 0.1502 0.0226 0.0059 -0.0008 0.0000 0.0038 0.0006 -0.399 + 160 1.6830 26.5957 9.9468 0.1211 0.1372 0.0553 0.0048 -0.0023 0.0000 0.0031 0.0003 -0.406 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = 0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 + CDsurf = 0.00000 Cnsurf = 0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.805 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.273 - 163 0.0000 34.0626 12.7394 -0.0000 0.0001 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.148 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.059 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 0.061 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.362 - 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.463 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.537 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.610 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.689 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 + 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.882 + 165 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.679 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.001 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.287 + 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.434 + 169 0.0000 31.2096 11.6724 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.550 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.668 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_06_05.txt b/regression/scripts/AVL/avl_files/strip_forces_case_06_05.txt index 985bd0816c..2a94d35c27 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_06_05.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_06_05.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.54076 Clsurf = -0.10911 - CYsurf = -0.03261 Cmsurf = -0.51272 - CDsurf = 0.02447 Cnsurf = -0.01053 - CDisurf = 0.02447 CDvsurf = 0.00000 + CLsurf = 0.54180 Clsurf = -0.10921 + CYsurf = -0.03265 Cmsurf = -0.51316 + CDsurf = 0.02452 Cnsurf = -0.01055 + CDisurf = 0.02452 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.05740 CDsurf = 0.04776 + CLsurf = 1.05943 CDsurf = 0.04786 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 6.9673 0.1913 0.9536 0.7386 1.3571 0.0000 -0.0804 -0.2501 0.359 - 2 0.1025 7.6885 1.0492 5.9568 0.1911 0.9728 0.7535 0.2203 0.0000 -0.0733 -0.2191 0.347 - 3 0.2837 7.5620 1.7073 5.8738 0.1898 0.9876 0.7649 0.1437 0.0000 -0.0708 -0.2175 0.343 - 4 0.5530 7.3741 2.3052 5.8410 0.1869 1.0101 0.7823 0.1276 0.0000 -0.0667 -0.2174 0.335 - 5 0.9075 7.1267 2.8223 5.8013 0.1812 1.0399 0.8055 0.1193 0.0000 -0.0616 -0.2178 0.327 - 6 1.3432 6.8226 3.2414 5.7389 0.1688 1.0774 0.8345 0.1055 0.0000 -0.0566 -0.2192 0.318 - 7 1.8554 6.4651 3.5491 5.6567 0.1441 1.1229 0.8697 0.0957 0.0000 -0.0518 -0.2224 0.310 - 8 2.4386 6.0582 3.7368 5.5335 0.1195 1.1744 0.9096 0.0867 0.0000 -0.0483 -0.2274 0.303 - 9 3.0862 5.6062 3.8005 5.3651 0.1065 1.2342 0.9560 0.0668 0.0000 -0.0464 -0.2348 0.299 - 10 3.7613 5.1351 3.4440 5.1877 0.0951 1.3043 1.0102 0.0620 0.0000 -0.0457 -0.2452 0.295 - 11 4.4532 4.6522 3.3149 4.9640 0.0813 1.3817 1.0701 0.0400 0.0000 -0.0468 -0.2578 0.294 - 12 5.1831 4.1429 3.0930 4.7261 0.0592 1.4811 1.1470 0.0188 0.0000 -0.0471 -0.2733 0.291 - 13 6.0123 3.7903 3.4706 4.4709 0.0433 1.4572 1.1873 0.0092 0.0000 -0.0387 -0.3010 0.283 - 14 6.9353 3.6075 3.3775 4.2710 0.0427 1.4627 1.1917 0.0092 0.0000 -0.0357 -0.2993 0.280 - 15 7.8737 3.4215 3.2389 4.0853 0.0397 1.4755 1.2022 0.0065 0.0000 -0.0334 -0.2996 0.278 - 16 8.8172 3.2345 3.0619 3.9005 0.0379 1.4907 1.2146 0.0031 0.0000 -0.0317 -0.3008 0.276 - 17 9.7556 3.0486 2.8543 3.7138 0.0382 1.5065 1.2274 -0.0003 0.0000 -0.0302 -0.3023 0.275 - 18 10.6786 2.8657 2.6240 3.5274 0.0400 1.5227 1.2406 -0.0036 0.0000 -0.0286 -0.3037 0.273 - 19 11.5760 2.6879 2.3787 3.3354 0.0431 1.5355 1.2511 -0.0071 0.0000 -0.0267 -0.3043 0.271 - 20 12.4328 2.5181 2.1010 3.1388 0.0473 1.5430 1.2571 -0.0106 0.0000 -0.0240 -0.3032 0.269 - 21 13.2400 2.3582 1.8520 2.9349 0.0530 1.5411 1.2556 -0.0141 0.0000 -0.0201 -0.2993 0.266 - 22 13.9941 2.2087 1.6074 2.7184 0.0601 1.5246 1.2421 -0.0177 0.0000 -0.0143 -0.2911 0.262 - 23 14.6868 2.0715 1.3716 2.4832 0.0683 1.4856 1.2104 -0.0213 0.0000 -0.0063 -0.2767 0.255 - 24 15.3105 1.9479 1.1479 2.2232 0.0772 1.4151 1.1529 -0.0246 0.0000 0.0031 -0.2554 0.247 - 25 15.8583 1.8393 0.9381 1.9314 0.0861 1.3023 1.0611 -0.0255 0.0000 0.0098 -0.2289 0.241 - 26 16.3244 1.7470 0.7427 1.6069 0.0957 1.1400 0.9288 -0.0166 0.0000 0.0042 -0.2044 0.245 - 27 16.6722 1.4928 0.4131 1.2640 0.1048 2.8852 0.8636 -0.0839 0.0000 -0.0015 -0.1064 0.252 - 28 16.9098 1.1466 0.2292 0.9225 0.1152 2.7665 0.8281 -0.1404 0.0000 0.0375 -0.0833 0.205 - 29 17.0696 0.9138 0.1104 0.5624 0.1218 2.1499 0.6435 -0.1873 0.0000 0.0681 -0.0458 0.144 - 30 17.1499 0.7967 0.0322 0.1890 0.1247 0.8565 0.2564 -0.1387 0.0000 0.0398 -0.0115 0.095 + 1 0.0114 7.7520 0.3539 6.9991 0.1909 0.9579 0.7419 1.3635 0.0000 -0.0829 -0.2530 0.362 + 2 0.1025 7.6885 1.0491 5.9774 0.1906 0.9762 0.7561 0.2209 0.0000 -0.0749 -0.2209 0.349 + 3 0.2837 7.5620 1.7073 5.8935 0.1896 0.9910 0.7676 0.1433 0.0000 -0.0724 -0.2193 0.344 + 4 0.5530 7.3741 2.3052 5.8596 0.1871 1.0138 0.7852 0.1247 0.0000 -0.0684 -0.2192 0.337 + 5 0.9075 7.1267 2.8223 5.8221 0.1816 1.0440 0.8086 0.1179 0.0000 -0.0634 -0.2198 0.328 + 6 1.3432 6.8226 3.2414 5.7664 0.1695 1.0818 0.8379 0.1108 0.0000 -0.0582 -0.2214 0.319 + 7 1.8554 6.4651 3.5491 5.6780 0.1450 1.1270 0.8729 0.0975 0.0000 -0.0536 -0.2244 0.311 + 8 2.4386 6.0582 3.7368 5.5531 0.1206 1.1787 0.9130 0.0857 0.0000 -0.0500 -0.2295 0.305 + 9 3.0862 5.6062 3.8005 5.3900 0.1082 1.2395 0.9600 0.0703 0.0000 -0.0479 -0.2370 0.300 + 10 3.7613 5.1351 3.4440 5.2335 0.0966 1.3169 1.0199 0.0559 0.0000 -0.0457 -0.2471 0.295 + 11 4.4532 4.6522 3.3149 4.9614 0.0813 1.3805 1.0692 0.0428 0.0000 -0.0445 -0.2558 0.292 + 12 5.1831 4.1429 3.0930 4.7297 0.0579 1.4824 1.1481 0.0176 0.0000 -0.0456 -0.2722 0.290 + 13 6.0123 3.7903 3.4706 4.4778 0.0427 1.4594 1.1891 0.0095 0.0000 -0.0366 -0.2995 0.281 + 14 6.9353 3.6075 3.3775 4.2759 0.0423 1.4644 1.1931 0.0090 0.0000 -0.0334 -0.2976 0.278 + 15 7.8737 3.4215 3.2389 4.0878 0.0395 1.4764 1.2029 0.0067 0.0000 -0.0310 -0.2977 0.276 + 16 8.8172 3.2345 3.0619 3.9026 0.0377 1.4916 1.2152 0.0030 0.0000 -0.0292 -0.2987 0.274 + 17 9.7556 3.0486 2.8543 3.7163 0.0381 1.5075 1.2282 -0.0002 0.0000 -0.0277 -0.3002 0.273 + 18 10.6786 2.8657 2.6239 3.5291 0.0400 1.5234 1.2412 -0.0038 0.0000 -0.0260 -0.3016 0.271 + 19 11.5760 2.6879 2.3787 3.3369 0.0430 1.5363 1.2517 -0.0072 0.0000 -0.0241 -0.3021 0.269 + 20 12.4328 2.5181 2.1010 3.1401 0.0473 1.5437 1.2577 -0.0108 0.0000 -0.0214 -0.3010 0.267 + 21 13.2400 2.3582 1.8520 2.9359 0.0529 1.5417 1.2561 -0.0143 0.0000 -0.0175 -0.2971 0.264 + 22 13.9941 2.2087 1.6074 2.7193 0.0600 1.5252 1.2426 -0.0179 0.0000 -0.0117 -0.2888 0.259 + 23 14.6868 2.0715 1.3716 2.4835 0.0683 1.4858 1.2106 -0.0215 0.0000 -0.0036 -0.2744 0.253 + 24 15.3105 1.9479 1.1479 2.2229 0.0771 1.4149 1.1528 -0.0249 0.0000 0.0058 -0.2530 0.245 + 25 15.8583 1.8393 0.9381 1.9310 0.0860 1.3021 1.0609 -0.0258 0.0000 0.0124 -0.2265 0.238 + 26 16.3244 1.7470 0.7427 1.6057 0.0950 1.1392 0.9281 -0.0170 0.0000 0.0069 -0.2019 0.243 + 27 16.6722 1.4928 0.4131 1.2629 0.1043 2.8829 0.8629 -0.0846 0.0000 0.0006 -0.1054 0.249 + 28 16.9098 1.1466 0.2292 0.9217 0.1149 2.7645 0.8275 -0.1410 0.0000 0.0393 -0.0824 0.203 + 29 17.0696 0.9138 0.1104 0.5620 0.1216 2.1488 0.6432 -0.1880 0.0000 0.0693 -0.0452 0.142 + 30 17.1499 0.7967 0.0322 0.1890 0.1254 0.8567 0.2564 -0.1397 0.0000 0.0402 -0.0113 0.093 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.54076 Clsurf = 0.10911 - CYsurf = 0.03261 Cmsurf = -0.51272 - CDsurf = 0.02447 Cnsurf = 0.01053 - CDisurf = 0.02447 CDvsurf = 0.00000 + CLsurf = 0.54180 Clsurf = 0.10921 + CYsurf = 0.03265 Cmsurf = -0.51316 + CDsurf = 0.02452 Cnsurf = 0.01055 + CDisurf = 0.02452 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.05739 CDsurf = 0.04776 + CLsurf = 1.05943 CDsurf = 0.04786 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 6.9673 0.1915 0.9536 0.7386 1.3572 0.0000 -0.0804 0.2501 0.359 - 32 -0.1025 7.6885 1.0492 5.9568 0.1911 0.9728 0.7535 0.2202 0.0000 -0.0733 0.2191 0.347 - 33 -0.2837 7.5620 1.7073 5.8738 0.1898 0.9876 0.7649 0.1437 0.0000 -0.0708 0.2175 0.343 - 34 -0.5530 7.3741 2.3052 5.8410 0.1869 1.0101 0.7823 0.1276 0.0000 -0.0667 0.2174 0.335 - 35 -0.9075 7.1267 2.8223 5.8013 0.1812 1.0399 0.8055 0.1193 0.0000 -0.0616 0.2178 0.327 - 36 -1.3432 6.8226 3.2414 5.7389 0.1688 1.0774 0.8345 0.1055 0.0000 -0.0566 0.2192 0.318 - 37 -1.8554 6.4651 3.5491 5.6567 0.1441 1.1229 0.8697 0.0957 0.0000 -0.0518 0.2224 0.310 - 38 -2.4386 6.0582 3.7368 5.5335 0.1195 1.1744 0.9096 0.0867 0.0000 -0.0483 0.2274 0.303 - 39 -3.0862 5.6062 3.8005 5.3651 0.1065 1.2342 0.9560 0.0668 0.0000 -0.0464 0.2348 0.299 - 40 -3.7613 5.1351 3.4440 5.1876 0.0951 1.3043 1.0102 0.0620 0.0000 -0.0457 0.2452 0.295 - 41 -4.4532 4.6522 3.3149 4.9640 0.0813 1.3817 1.0701 0.0400 0.0000 -0.0468 0.2578 0.294 - 42 -5.1831 4.1429 3.0930 4.7261 0.0592 1.4810 1.1470 0.0188 0.0000 -0.0471 0.2733 0.291 - 43 -6.0123 3.7903 3.4706 4.4709 0.0433 1.4572 1.1873 0.0092 0.0000 -0.0387 0.3010 0.283 - 44 -6.9353 3.6075 3.3775 4.2710 0.0427 1.4627 1.1917 0.0092 0.0000 -0.0357 0.2993 0.280 - 45 -7.8737 3.4215 3.2389 4.0853 0.0397 1.4755 1.2022 0.0065 0.0000 -0.0334 0.2996 0.278 - 46 -8.8172 3.2345 3.0619 3.9005 0.0379 1.4907 1.2146 0.0031 0.0000 -0.0317 0.3008 0.276 - 47 -9.7556 3.0486 2.8543 3.7138 0.0382 1.5065 1.2274 -0.0003 0.0000 -0.0302 0.3023 0.275 - 48 -10.6786 2.8657 2.6240 3.5274 0.0400 1.5227 1.2406 -0.0036 0.0000 -0.0286 0.3037 0.273 - 49 -11.5760 2.6879 2.3787 3.3353 0.0431 1.5355 1.2511 -0.0071 0.0000 -0.0267 0.3043 0.271 - 50 -12.4328 2.5181 2.1010 3.1388 0.0473 1.5430 1.2571 -0.0106 0.0000 -0.0240 0.3032 0.269 - 51 -13.2400 2.3582 1.8520 2.9349 0.0530 1.5411 1.2556 -0.0141 0.0000 -0.0201 0.2993 0.266 - 52 -13.9941 2.2087 1.6074 2.7183 0.0601 1.5246 1.2421 -0.0177 0.0000 -0.0143 0.2911 0.262 - 53 -14.6868 2.0715 1.3716 2.4832 0.0683 1.4856 1.2104 -0.0214 0.0000 -0.0063 0.2767 0.255 - 54 -15.3105 1.9479 1.1479 2.2231 0.0772 1.4151 1.1529 -0.0246 0.0000 0.0031 0.2554 0.247 - 55 -15.8583 1.8393 0.9381 1.9313 0.0861 1.3023 1.0610 -0.0255 0.0000 0.0098 0.2289 0.241 - 56 -16.3244 1.7470 0.7427 1.6069 0.0957 1.1400 0.9288 -0.0166 0.0000 0.0042 0.2044 0.245 - 57 -16.6722 1.4928 0.4131 1.2640 0.1048 2.8851 0.8636 -0.0838 0.0000 -0.0015 0.1064 0.252 - 58 -16.9098 1.1466 0.2292 0.9224 0.1152 2.7664 0.8281 -0.1404 0.0000 0.0375 0.0833 0.205 - 59 -17.0696 0.9138 0.1104 0.5624 0.1218 2.1499 0.6435 -0.1873 0.0000 0.0681 0.0458 0.144 - 60 -17.1499 0.7967 0.0322 0.1890 0.1247 0.8565 0.2564 -0.1387 0.0000 0.0398 0.0115 0.095 + 31 -0.0114 7.7520 0.3539 6.9991 0.1909 0.9579 0.7419 1.3635 0.0000 -0.0829 0.2530 0.362 + 32 -0.1025 7.6885 1.0491 5.9774 0.1906 0.9762 0.7561 0.2209 0.0000 -0.0749 0.2209 0.349 + 33 -0.2837 7.5620 1.7073 5.8935 0.1896 0.9910 0.7676 0.1433 0.0000 -0.0724 0.2193 0.344 + 34 -0.5530 7.3741 2.3052 5.8595 0.1871 1.0138 0.7852 0.1247 0.0000 -0.0684 0.2192 0.337 + 35 -0.9075 7.1267 2.8223 5.8221 0.1816 1.0440 0.8086 0.1179 0.0000 -0.0634 0.2198 0.328 + 36 -1.3432 6.8226 3.2414 5.7664 0.1695 1.0818 0.8379 0.1108 0.0000 -0.0582 0.2214 0.319 + 37 -1.8554 6.4651 3.5491 5.6780 0.1450 1.1270 0.8729 0.0975 0.0000 -0.0536 0.2244 0.311 + 38 -2.4386 6.0582 3.7368 5.5531 0.1206 1.1787 0.9130 0.0857 0.0000 -0.0500 0.2295 0.305 + 39 -3.0862 5.6062 3.8005 5.3900 0.1082 1.2395 0.9600 0.0703 0.0000 -0.0479 0.2370 0.300 + 40 -3.7613 5.1351 3.4440 5.2335 0.0966 1.3169 1.0199 0.0559 0.0000 -0.0457 0.2471 0.295 + 41 -4.4532 4.6522 3.3149 4.9614 0.0813 1.3805 1.0692 0.0428 0.0000 -0.0445 0.2558 0.292 + 42 -5.1831 4.1429 3.0930 4.7297 0.0579 1.4824 1.1481 0.0176 0.0000 -0.0456 0.2722 0.290 + 43 -6.0123 3.7903 3.4706 4.4778 0.0427 1.4594 1.1891 0.0095 0.0000 -0.0366 0.2995 0.281 + 44 -6.9353 3.6075 3.3775 4.2759 0.0423 1.4644 1.1931 0.0090 0.0000 -0.0334 0.2976 0.278 + 45 -7.8737 3.4215 3.2389 4.0878 0.0395 1.4764 1.2029 0.0067 0.0000 -0.0310 0.2977 0.276 + 46 -8.8172 3.2345 3.0619 3.9026 0.0377 1.4916 1.2152 0.0030 0.0000 -0.0292 0.2987 0.274 + 47 -9.7556 3.0486 2.8543 3.7163 0.0381 1.5075 1.2282 -0.0002 0.0000 -0.0277 0.3002 0.273 + 48 -10.6786 2.8657 2.6239 3.5291 0.0400 1.5234 1.2412 -0.0038 0.0000 -0.0260 0.3016 0.271 + 49 -11.5760 2.6879 2.3787 3.3369 0.0430 1.5363 1.2517 -0.0072 0.0000 -0.0241 0.3021 0.269 + 50 -12.4328 2.5181 2.1010 3.1401 0.0473 1.5436 1.2577 -0.0108 0.0000 -0.0214 0.3010 0.267 + 51 -13.2400 2.3582 1.8520 2.9359 0.0529 1.5417 1.2561 -0.0143 0.0000 -0.0175 0.2971 0.264 + 52 -13.9941 2.2087 1.6074 2.7193 0.0600 1.5251 1.2426 -0.0179 0.0000 -0.0117 0.2888 0.259 + 53 -14.6868 2.0715 1.3716 2.4835 0.0683 1.4858 1.2106 -0.0215 0.0000 -0.0036 0.2744 0.253 + 54 -15.3105 1.9479 1.1479 2.2229 0.0771 1.4149 1.1528 -0.0249 0.0000 0.0058 0.2530 0.245 + 55 -15.8583 1.8393 0.9381 1.9310 0.0860 1.3021 1.0609 -0.0258 0.0000 0.0124 0.2265 0.238 + 56 -16.3244 1.7470 0.7427 1.6057 0.0950 1.1392 0.9281 -0.0170 0.0000 0.0069 0.2019 0.243 + 57 -16.6722 1.4928 0.4131 1.2629 0.1043 2.8829 0.8629 -0.0846 0.0000 0.0006 0.1054 0.249 + 58 -16.9098 1.1466 0.2292 0.9217 0.1149 2.7645 0.8275 -0.1410 0.0000 0.0393 0.0824 0.203 + 59 -17.0696 0.9138 0.1104 0.5620 0.1216 2.1488 0.6432 -0.1880 0.0000 0.0693 0.0452 0.142 + 60 -17.1499 0.7967 0.0322 0.1890 0.1254 0.8567 0.2564 -0.1397 0.0000 0.0402 0.0113 0.093 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04462 Clsurf = -0.00468 - CYsurf = -0.00745 Cmsurf = -0.21867 - CDsurf = 0.00399 Cnsurf = 0.00418 - CDisurf = 0.00399 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04436 Clsurf = -0.00466 + CYsurf = -0.00741 Cmsurf = -0.21742 + CDsurf = 0.00397 Cnsurf = 0.00416 + CDisurf = 0.00397 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.27224 CDsurf = 0.02403 + CLsurf = 0.27065 CDsurf = 0.02391 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 1.1415 0.1411 0.3259 0.2487 0.1675 0.0000 -0.0221 -0.0764 0.339 - 62 0.0418 4.2566 0.2392 0.9347 0.1415 0.2841 0.2168 0.0356 0.0000 -0.0194 -0.0641 0.340 - 63 0.1156 4.2274 0.3930 0.9184 0.1416 0.2826 0.2157 0.0261 0.0000 -0.0188 -0.0631 0.337 - 64 0.2254 4.1839 0.5386 0.9146 0.1410 0.2846 0.2172 0.0244 0.0000 -0.0178 -0.0626 0.332 - 65 0.3698 4.1268 0.6730 0.9118 0.1397 0.2878 0.2197 0.0239 0.0000 -0.0164 -0.0619 0.325 - 66 0.5474 4.0565 0.7936 0.9104 0.1374 0.2924 0.2232 0.0239 0.0000 -0.0148 -0.0613 0.316 - 67 0.7617 3.9717 0.9441 0.9080 0.1340 0.2980 0.2274 0.0237 0.0000 -0.0130 -0.0608 0.307 - 68 1.0116 3.8728 1.0344 0.9040 0.1292 0.3043 0.2322 0.0237 0.0000 -0.0114 -0.0605 0.299 - 69 1.2891 3.7630 1.1046 0.8991 0.1234 0.3116 0.2378 0.0238 0.0000 -0.0098 -0.0604 0.291 - 70 1.5912 3.6435 1.1542 0.8937 0.1168 0.3199 0.2442 0.0239 0.0000 -0.0084 -0.0605 0.284 - 71 1.9146 3.5155 1.1831 0.8867 0.1103 0.3291 0.2511 0.0240 0.0000 -0.0071 -0.0610 0.278 - 72 2.2558 3.3805 1.1921 0.8793 0.1046 0.3395 0.2591 0.0243 0.0000 -0.0059 -0.0617 0.273 - 73 2.6109 3.2400 1.1821 0.8714 0.1000 0.3511 0.2679 0.0246 0.0000 -0.0048 -0.0627 0.268 - 74 2.9762 3.0955 1.1548 0.8629 0.0968 0.3640 0.2778 0.0249 0.0000 -0.0036 -0.0639 0.263 - 75 3.3476 2.9485 1.1122 0.8530 0.0946 0.3778 0.2883 0.0252 0.0000 -0.0024 -0.0652 0.258 - 76 3.7210 2.8008 1.0564 0.8415 0.0932 0.3925 0.2996 0.0254 0.0000 -0.0011 -0.0665 0.254 - 77 4.0924 2.6538 0.9900 0.8273 0.0926 0.4074 0.3109 0.0256 0.0000 0.0004 -0.0677 0.249 - 78 4.4577 2.5093 0.9155 0.8096 0.0925 0.4218 0.3219 0.0256 0.0000 0.0022 -0.0686 0.243 - 79 4.8128 2.3687 0.8353 0.7869 0.0931 0.4344 0.3315 0.0253 0.0000 0.0044 -0.0688 0.237 - 80 5.1540 2.2338 0.7518 0.7591 0.0941 0.4446 0.3393 0.0248 0.0000 0.0071 -0.0682 0.229 - 81 5.4774 2.1058 0.6671 0.7249 0.0955 0.4506 0.3439 0.0239 0.0000 0.0103 -0.0665 0.220 - 82 5.7795 1.9862 0.5830 0.6835 0.0972 0.4506 0.3439 0.0225 0.0000 0.0141 -0.0633 0.209 - 83 6.0570 1.8764 0.5012 0.6343 0.0989 0.4429 0.3380 0.0207 0.0000 0.0181 -0.0586 0.196 - 84 6.3069 1.7776 0.4225 0.5780 0.1006 0.4262 0.3253 0.0184 0.0000 0.0223 -0.0524 0.182 - 85 6.5264 1.6907 0.3478 0.5143 0.1021 0.3991 0.3046 0.0154 0.0000 0.0259 -0.0448 0.165 - 86 6.7314 1.6096 0.3326 0.4402 0.1035 0.3591 0.2740 0.0120 0.0000 0.0284 -0.0360 0.146 - 87 6.9144 1.5372 0.2507 0.3526 0.1047 0.3016 0.2301 0.0078 0.0000 0.0286 -0.0262 0.126 - 88 7.0535 1.4822 0.1746 0.2572 0.1056 0.2285 0.1744 0.0034 0.0000 0.0251 -0.0170 0.106 - 89 7.1471 1.4451 0.1029 0.1564 0.1062 0.1429 0.1091 -0.0002 0.0000 0.0174 -0.0091 0.091 - 90 7.1941 1.4265 0.0340 0.0525 0.1065 0.0492 0.0375 -0.0037 0.0000 0.0062 -0.0029 0.085 + 61 0.0047 4.2713 0.0803 1.1313 0.1412 0.3231 0.2466 0.1651 0.0000 -0.0219 -0.0758 0.339 + 62 0.0418 4.2566 0.2392 0.9275 0.1416 0.2820 0.2152 0.0353 0.0000 -0.0193 -0.0637 0.340 + 63 0.1156 4.2274 0.3930 0.9111 0.1417 0.2803 0.2139 0.0259 0.0000 -0.0187 -0.0627 0.338 + 64 0.2254 4.1839 0.5386 0.9075 0.1411 0.2824 0.2156 0.0241 0.0000 -0.0177 -0.0621 0.332 + 65 0.3698 4.1268 0.6730 0.9053 0.1398 0.2858 0.2181 0.0237 0.0000 -0.0163 -0.0615 0.325 + 66 0.5474 4.0565 0.7936 0.9037 0.1376 0.2903 0.2215 0.0236 0.0000 -0.0147 -0.0609 0.316 + 67 0.7617 3.9717 0.9441 0.9012 0.1341 0.2957 0.2257 0.0236 0.0000 -0.0130 -0.0604 0.308 + 68 1.0116 3.8728 1.0344 0.8970 0.1294 0.3019 0.2304 0.0235 0.0000 -0.0113 -0.0600 0.299 + 69 1.2891 3.7630 1.1046 0.8922 0.1235 0.3092 0.2360 0.0236 0.0000 -0.0098 -0.0599 0.291 + 70 1.5912 3.6435 1.1542 0.8866 0.1169 0.3174 0.2422 0.0238 0.0000 -0.0084 -0.0601 0.285 + 71 1.9146 3.5155 1.1831 0.8803 0.1104 0.3267 0.2493 0.0240 0.0000 -0.0071 -0.0606 0.278 + 72 2.2558 3.3805 1.1921 0.8731 0.1047 0.3370 0.2572 0.0241 0.0000 -0.0059 -0.0613 0.273 + 73 2.6109 3.2400 1.1821 0.8655 0.1002 0.3487 0.2661 0.0244 0.0000 -0.0048 -0.0623 0.268 + 74 2.9762 3.0955 1.1548 0.8575 0.0969 0.3617 0.2760 0.0248 0.0000 -0.0037 -0.0635 0.263 + 75 3.3476 2.9485 1.1122 0.8478 0.0947 0.3755 0.2866 0.0251 0.0000 -0.0025 -0.0648 0.259 + 76 3.7210 2.8008 1.0564 0.8365 0.0933 0.3902 0.2978 0.0254 0.0000 -0.0012 -0.0662 0.254 + 77 4.0924 2.6538 0.9900 0.8228 0.0926 0.4052 0.3092 0.0255 0.0000 0.0004 -0.0674 0.249 + 78 4.4577 2.5093 0.9155 0.8055 0.0926 0.4197 0.3203 0.0254 0.0000 0.0022 -0.0683 0.243 + 79 4.8128 2.3687 0.8353 0.7836 0.0932 0.4326 0.3302 0.0253 0.0000 0.0044 -0.0685 0.237 + 80 5.1540 2.2338 0.7518 0.7563 0.0942 0.4429 0.3380 0.0248 0.0000 0.0071 -0.0680 0.229 + 81 5.4774 2.1058 0.6671 0.7224 0.0956 0.4490 0.3427 0.0239 0.0000 0.0103 -0.0663 0.220 + 82 5.7795 1.9862 0.5830 0.6810 0.0972 0.4490 0.3426 0.0225 0.0000 0.0140 -0.0631 0.209 + 83 6.0570 1.8764 0.5012 0.6324 0.0989 0.4416 0.3370 0.0207 0.0000 0.0181 -0.0584 0.196 + 84 6.3069 1.7776 0.4225 0.5765 0.1006 0.4251 0.3245 0.0183 0.0000 0.0222 -0.0522 0.182 + 85 6.5264 1.6907 0.3478 0.5131 0.1021 0.3981 0.3038 0.0154 0.0000 0.0258 -0.0447 0.165 + 86 6.7314 1.6096 0.3326 0.4393 0.1035 0.3583 0.2735 0.0120 0.0000 0.0283 -0.0359 0.146 + 87 6.9144 1.5372 0.2507 0.3519 0.1047 0.3009 0.2297 0.0079 0.0000 0.0286 -0.0261 0.126 + 88 7.0535 1.4822 0.1746 0.2566 0.1056 0.2280 0.1740 0.0034 0.0000 0.0250 -0.0169 0.106 + 89 7.1471 1.4451 0.1029 0.1561 0.1062 0.1427 0.1089 -0.0002 0.0000 0.0173 -0.0091 0.091 + 90 7.1941 1.4265 0.0340 0.0524 0.1065 0.0491 0.0375 -0.0037 0.0000 0.0062 -0.0029 0.085 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.04462 Clsurf = 0.00468 - CYsurf = 0.00745 Cmsurf = -0.21866 - CDsurf = 0.00399 Cnsurf = -0.00418 - CDisurf = 0.00399 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.04436 Clsurf = 0.00466 + CYsurf = 0.00741 Cmsurf = -0.21741 + CDsurf = 0.00397 Cnsurf = -0.00416 + CDisurf = 0.00397 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.27223 CDsurf = 0.02403 + CLsurf = 0.27065 CDsurf = 0.02391 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 1.1415 0.1411 0.3259 0.2487 0.1675 0.0000 -0.0221 0.0764 0.339 - 92 -0.0418 4.2566 0.2392 0.9347 0.1415 0.2841 0.2168 0.0356 0.0000 -0.0194 0.0641 0.340 - 93 -0.1156 4.2274 0.3930 0.9184 0.1416 0.2826 0.2157 0.0261 0.0000 -0.0188 0.0631 0.337 - 94 -0.2254 4.1839 0.5386 0.9146 0.1410 0.2846 0.2172 0.0244 0.0000 -0.0178 0.0626 0.332 - 95 -0.3698 4.1268 0.6730 0.9118 0.1397 0.2878 0.2197 0.0239 0.0000 -0.0164 0.0619 0.325 - 96 -0.5474 4.0565 0.7936 0.9104 0.1374 0.2924 0.2232 0.0239 0.0000 -0.0148 0.0613 0.316 - 97 -0.7617 3.9717 0.9441 0.9080 0.1340 0.2980 0.2274 0.0237 0.0000 -0.0130 0.0608 0.307 - 98 -1.0116 3.8728 1.0344 0.9040 0.1292 0.3043 0.2322 0.0237 0.0000 -0.0114 0.0605 0.299 - 99 -1.2891 3.7630 1.1046 0.8991 0.1234 0.3116 0.2378 0.0238 0.0000 -0.0098 0.0604 0.291 - 100 -1.5912 3.6435 1.1542 0.8936 0.1168 0.3199 0.2442 0.0239 0.0000 -0.0084 0.0605 0.284 - 101 -1.9146 3.5155 1.1831 0.8866 0.1103 0.3291 0.2511 0.0240 0.0000 -0.0071 0.0610 0.278 - 102 -2.2558 3.3805 1.1921 0.8793 0.1046 0.3394 0.2591 0.0243 0.0000 -0.0059 0.0617 0.273 - 103 -2.6109 3.2400 1.1821 0.8714 0.1000 0.3511 0.2679 0.0246 0.0000 -0.0048 0.0627 0.268 - 104 -2.9762 3.0955 1.1548 0.8629 0.0968 0.3640 0.2778 0.0249 0.0000 -0.0036 0.0639 0.263 - 105 -3.3476 2.9485 1.1122 0.8529 0.0946 0.3778 0.2883 0.0252 0.0000 -0.0024 0.0652 0.258 - 106 -3.7210 2.8008 1.0564 0.8415 0.0932 0.3925 0.2995 0.0254 0.0000 -0.0011 0.0665 0.254 - 107 -4.0924 2.6538 0.9900 0.8273 0.0926 0.4074 0.3109 0.0256 0.0000 0.0004 0.0677 0.249 - 108 -4.4577 2.5093 0.9155 0.8095 0.0925 0.4218 0.3219 0.0256 0.0000 0.0022 0.0686 0.243 - 109 -4.8128 2.3687 0.8353 0.7868 0.0931 0.4344 0.3315 0.0253 0.0000 0.0044 0.0688 0.237 - 110 -5.1540 2.2338 0.7518 0.7591 0.0941 0.4446 0.3393 0.0248 0.0000 0.0071 0.0682 0.229 - 111 -5.4774 2.1058 0.6671 0.7249 0.0955 0.4506 0.3439 0.0239 0.0000 0.0103 0.0665 0.220 - 112 -5.7795 1.9862 0.5830 0.6835 0.0972 0.4506 0.3439 0.0225 0.0000 0.0141 0.0633 0.209 - 113 -6.0570 1.8764 0.5012 0.6343 0.0989 0.4429 0.3380 0.0207 0.0000 0.0181 0.0586 0.196 - 114 -6.3069 1.7776 0.4225 0.5780 0.1006 0.4262 0.3253 0.0184 0.0000 0.0223 0.0524 0.182 - 115 -6.5264 1.6907 0.3478 0.5143 0.1021 0.3991 0.3046 0.0154 0.0000 0.0259 0.0448 0.165 - 116 -6.7314 1.6096 0.3326 0.4402 0.1035 0.3591 0.2740 0.0120 0.0000 0.0284 0.0360 0.146 - 117 -6.9144 1.5372 0.2507 0.3526 0.1047 0.3016 0.2301 0.0078 0.0000 0.0286 0.0262 0.126 - 118 -7.0535 1.4822 0.1746 0.2572 0.1056 0.2285 0.1744 0.0034 0.0000 0.0251 0.0170 0.106 - 119 -7.1471 1.4451 0.1029 0.1564 0.1062 0.1429 0.1091 -0.0002 0.0000 0.0174 0.0091 0.091 - 120 -7.1941 1.4265 0.0340 0.0525 0.1065 0.0492 0.0375 -0.0037 0.0000 0.0062 0.0029 0.085 + 91 -0.0047 4.2713 0.0803 1.1313 0.1412 0.3231 0.2466 0.1651 0.0000 -0.0219 0.0758 0.339 + 92 -0.0418 4.2566 0.2392 0.9275 0.1416 0.2820 0.2152 0.0353 0.0000 -0.0193 0.0637 0.340 + 93 -0.1156 4.2274 0.3930 0.9111 0.1417 0.2803 0.2139 0.0259 0.0000 -0.0187 0.0627 0.338 + 94 -0.2254 4.1839 0.5386 0.9075 0.1411 0.2824 0.2156 0.0241 0.0000 -0.0177 0.0621 0.332 + 95 -0.3698 4.1268 0.6730 0.9053 0.1398 0.2858 0.2181 0.0237 0.0000 -0.0163 0.0615 0.325 + 96 -0.5474 4.0565 0.7936 0.9037 0.1376 0.2903 0.2215 0.0236 0.0000 -0.0147 0.0609 0.316 + 97 -0.7617 3.9717 0.9441 0.9012 0.1341 0.2957 0.2257 0.0236 0.0000 -0.0130 0.0604 0.308 + 98 -1.0116 3.8728 1.0344 0.8970 0.1294 0.3019 0.2304 0.0235 0.0000 -0.0113 0.0600 0.299 + 99 -1.2891 3.7630 1.1046 0.8922 0.1235 0.3092 0.2360 0.0236 0.0000 -0.0098 0.0599 0.291 + 100 -1.5912 3.6435 1.1542 0.8866 0.1169 0.3174 0.2422 0.0238 0.0000 -0.0084 0.0601 0.285 + 101 -1.9146 3.5155 1.1831 0.8803 0.1104 0.3267 0.2493 0.0240 0.0000 -0.0071 0.0606 0.278 + 102 -2.2558 3.3805 1.1921 0.8731 0.1047 0.3370 0.2572 0.0241 0.0000 -0.0059 0.0613 0.273 + 103 -2.6109 3.2400 1.1821 0.8655 0.1002 0.3487 0.2661 0.0244 0.0000 -0.0048 0.0623 0.268 + 104 -2.9762 3.0955 1.1548 0.8575 0.0969 0.3617 0.2760 0.0248 0.0000 -0.0037 0.0635 0.263 + 105 -3.3476 2.9485 1.1122 0.8478 0.0947 0.3755 0.2866 0.0251 0.0000 -0.0025 0.0648 0.259 + 106 -3.7210 2.8008 1.0564 0.8365 0.0933 0.3902 0.2978 0.0254 0.0000 -0.0012 0.0662 0.254 + 107 -4.0924 2.6538 0.9900 0.8228 0.0926 0.4052 0.3092 0.0255 0.0000 0.0004 0.0674 0.249 + 108 -4.4577 2.5093 0.9155 0.8055 0.0926 0.4197 0.3203 0.0254 0.0000 0.0022 0.0683 0.243 + 109 -4.8128 2.3687 0.8353 0.7836 0.0932 0.4326 0.3302 0.0253 0.0000 0.0044 0.0685 0.237 + 110 -5.1540 2.2338 0.7518 0.7563 0.0942 0.4429 0.3380 0.0248 0.0000 0.0071 0.0680 0.229 + 111 -5.4774 2.1058 0.6671 0.7224 0.0956 0.4490 0.3427 0.0239 0.0000 0.0103 0.0663 0.220 + 112 -5.7795 1.9862 0.5830 0.6810 0.0972 0.4490 0.3426 0.0225 0.0000 0.0140 0.0631 0.209 + 113 -6.0570 1.8764 0.5012 0.6324 0.0989 0.4416 0.3370 0.0207 0.0000 0.0181 0.0584 0.196 + 114 -6.3069 1.7776 0.4225 0.5765 0.1006 0.4251 0.3245 0.0183 0.0000 0.0222 0.0522 0.182 + 115 -6.5264 1.6907 0.3478 0.5131 0.1021 0.3981 0.3038 0.0154 0.0000 0.0258 0.0447 0.165 + 116 -6.7314 1.6096 0.3326 0.4393 0.1035 0.3583 0.2734 0.0120 0.0000 0.0283 0.0359 0.146 + 117 -6.9144 1.5372 0.2507 0.3519 0.1047 0.3009 0.2297 0.0079 0.0000 0.0286 0.0261 0.126 + 118 -7.0535 1.4822 0.1746 0.2566 0.1056 0.2280 0.1740 0.0034 0.0000 0.0250 0.0169 0.106 + 119 -7.1471 1.4451 0.1029 0.1561 0.1062 0.1427 0.1089 -0.0002 0.0000 0.0173 0.0091 0.091 + 120 -7.1941 1.4265 0.0340 0.0524 0.1065 0.0491 0.0375 -0.0037 0.0000 0.0062 0.0029 0.085 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,68 +198,68 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.455 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.463 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.473 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.483 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.488 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.488 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.483 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.466 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.435 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.392 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.349 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.331 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.316 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.302 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.289 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.486 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.486 + 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.501 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.510 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.514 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.508 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.500 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.478 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.446 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.398 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.352 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.333 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.322 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.307 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.295 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.278 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.267 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.266 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.257 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.245 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.239 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.232 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.220 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.251 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.240 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.230 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.218 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.205 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.189 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.172 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.171 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.150 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.126 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.104 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.087 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.080 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.129 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.106 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.089 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.082 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01002 Clsurf = 0.00000 - CYsurf = 0.00000 Cmsurf = 0.06044 - CDsurf = -0.00014 Cnsurf = -0.00000 + CLsurf = 0.00995 Clsurf = -0.00000 + CYsurf = -0.00000 Cmsurf = 0.06051 + CDsurf = -0.00014 Cnsurf = 0.00000 CDisurf = -0.00014 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01010 CDsurf = -0.00014 + CLsurf = 0.01003 CDsurf = -0.00014 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.2253 0.1950 0.0967 0.0090 -0.0037 0.0000 0.0040 0.0003 -0.199 - 152 -1.3090 31.2096 11.6724 0.3252 0.2113 0.0398 0.0106 -0.0012 0.0000 0.0052 0.0006 -0.234 - 153 -0.9350 34.0626 12.7394 0.3521 0.1933 0.0249 0.0104 0.0000 0.0000 0.0064 0.0013 -0.367 - 154 -0.5610 36.1619 13.5246 0.3712 0.1900 0.0170 0.0102 0.0009 0.0000 0.0070 0.0020 -0.432 - 155 -0.1870 37.5332 14.0374 0.3837 0.1918 0.0116 0.0100 0.0022 0.0000 0.0071 0.0031 -0.459 - 156 0.1870 37.5332 14.0374 0.3837 0.1918 0.0116 0.0100 0.0022 0.0000 0.0071 0.0031 -0.459 - 157 0.5610 36.1619 13.5246 0.3712 0.1900 0.0170 0.0102 0.0009 0.0000 0.0070 0.0020 -0.432 - 158 0.9350 34.0626 12.7394 0.3521 0.1933 0.0249 0.0104 0.0000 0.0000 0.0064 0.0013 -0.367 - 159 1.3090 31.2096 11.6724 0.3252 0.2113 0.0398 0.0106 -0.0012 0.0000 0.0052 0.0006 -0.234 - 160 1.6830 26.5957 9.9468 0.2253 0.1950 0.0967 0.0090 -0.0037 0.0000 0.0040 0.0003 -0.199 + 151 -1.6830 26.5957 9.9468 0.2233 0.1949 0.0959 0.0089 -0.0037 0.0000 0.0041 0.0003 -0.206 + 152 -1.3090 31.2096 11.6724 0.3226 0.2112 0.0395 0.0106 -0.0012 0.0000 0.0052 0.0006 -0.240 + 153 -0.9350 34.0626 12.7394 0.3497 0.1935 0.0248 0.0103 0.0000 0.0000 0.0064 0.0013 -0.374 + 154 -0.5610 36.1619 13.5246 0.3689 0.1902 0.0169 0.0102 0.0009 0.0000 0.0070 0.0020 -0.438 + 155 -0.1870 37.5332 14.0374 0.3814 0.1920 0.0116 0.0100 0.0022 0.0000 0.0071 0.0032 -0.465 + 156 0.1870 37.5332 14.0374 0.3814 0.1920 0.0116 0.0100 0.0022 0.0000 0.0071 0.0032 -0.465 + 157 0.5610 36.1619 13.5246 0.3689 0.1902 0.0169 0.0102 0.0009 0.0000 0.0070 0.0020 -0.438 + 158 0.9350 34.0626 12.7394 0.3497 0.1935 0.0248 0.0103 0.0000 0.0000 0.0064 0.0013 -0.374 + 159 1.3090 31.2096 11.6724 0.3226 0.2112 0.0395 0.0106 -0.0012 0.0000 0.0052 0.0006 -0.240 + 160 1.6830 26.5957 9.9468 0.2233 0.1949 0.0959 0.0089 -0.0037 0.0000 0.0041 0.0003 -0.206 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 Surface area = 123.841202 Ave. chord = 33.112617 CLsurf = 0.00000 Clsurf = -0.00000 - CYsurf = 0.00000 Cmsurf = 0.00000 - CDsurf = 0.00000 Cnsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = -0.00000 + CDsurf = 0.00000 Cnsurf = 0.00000 CDisurf = 0.00000 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE @@ -269,13 +269,13 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 - 162 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0002 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.908 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.506 - 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.219 - 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.414 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.538 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.641 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.731 + 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 163 0.0000 34.0626 12.7394 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.675 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.131 + 168 0.0000 34.0626 12.7394 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.412 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.582 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.712 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/strip_forces_case_06_06.txt b/regression/scripts/AVL/avl_files/strip_forces_case_06_06.txt index cfe86bea4d..bf685a702f 100644 --- a/regression/scripts/AVL/avl_files/strip_forces_case_06_06.txt +++ b/regression/scripts/AVL/avl_files/strip_forces_case_06_06.txt @@ -7,186 +7,186 @@ Surface # 1 main_wing # Chordwise = 10 # Spanwise = 30 First strip = 1 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.71193 Clsurf = -0.14451 - CYsurf = -0.03789 Cmsurf = -0.67776 - CDsurf = 0.04188 Cnsurf = -0.02286 - CDisurf = 0.04188 CDvsurf = 0.00000 + CLsurf = 0.71301 Clsurf = -0.14461 + CYsurf = -0.03792 Cmsurf = -0.67813 + CDsurf = 0.04192 Cnsurf = -0.02290 + CDisurf = 0.04192 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.39143 CDsurf = 0.08175 + CLsurf = 1.39354 CDsurf = 0.08183 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 1 0.0114 7.7520 0.3539 9.3004 0.2499 1.0638 0.8256 2.2198 0.0000 -0.1072 -0.3346 0.380 - 2 0.1025 7.6885 1.0492 7.6342 0.2499 1.2182 0.9455 0.3550 0.0000 -0.0947 -0.2823 0.350 - 3 0.2837 7.5620 1.7073 7.5002 0.2488 1.2454 0.9666 0.2294 0.0000 -0.0913 -0.2793 0.344 - 4 0.5530 7.3741 2.3052 7.4544 0.2458 1.2761 0.9904 0.2038 0.0000 -0.0860 -0.2790 0.337 - 5 0.9075 7.1267 2.8223 7.4066 0.2392 1.3161 1.0214 0.1915 0.0000 -0.0793 -0.2795 0.328 - 6 1.3432 6.8226 3.2414 7.3342 0.2228 1.3675 1.0614 0.1707 0.0000 -0.0726 -0.2814 0.318 - 7 1.8554 6.4651 3.5491 7.2450 0.1867 1.4305 1.1102 0.1565 0.0000 -0.0662 -0.2857 0.310 - 8 2.4386 6.0582 3.7368 7.1072 0.1515 1.5021 1.1658 0.1438 0.0000 -0.0612 -0.2925 0.303 - 9 3.0862 5.6062 3.8005 6.9153 0.1366 1.5878 1.2324 0.1141 0.0000 -0.0581 -0.3024 0.297 - 10 3.7613 5.1351 3.4440 6.7218 0.1248 1.6879 1.3099 0.1089 0.0000 -0.0561 -0.3164 0.293 - 11 4.4532 4.6522 3.3149 6.4619 0.1092 1.8003 1.3972 0.0750 0.0000 -0.0561 -0.3330 0.290 - 12 5.1831 4.1429 3.0930 6.1887 0.0833 1.9448 1.5093 0.0426 0.0000 -0.0543 -0.3532 0.286 - 13 6.0123 3.7903 3.4706 5.8769 0.0638 1.9290 1.5696 0.0277 0.0000 -0.0395 -0.3882 0.275 - 14 6.9353 3.6075 3.3775 5.6339 0.0613 1.9435 1.5814 0.0253 0.0000 -0.0351 -0.3869 0.272 - 15 7.8737 3.4215 3.2389 5.4061 0.0559 1.9676 1.6010 0.0194 0.0000 -0.0318 -0.3882 0.270 - 16 8.8172 3.2345 3.0619 5.1746 0.0527 1.9938 1.6223 0.0124 0.0000 -0.0294 -0.3906 0.268 - 17 9.7556 3.0486 2.8543 4.9368 0.0527 2.0198 1.6435 0.0056 0.0000 -0.0274 -0.3933 0.267 - 18 10.6786 2.8657 2.6240 4.6983 0.0552 2.0463 1.6650 -0.0010 0.0000 -0.0251 -0.3959 0.265 - 19 11.5760 2.6879 2.3787 4.4493 0.0594 2.0675 1.6823 -0.0078 0.0000 -0.0225 -0.3972 0.263 - 20 12.4328 2.5181 2.1010 4.1923 0.0652 2.0809 1.6932 -0.0147 0.0000 -0.0188 -0.3962 0.261 - 21 13.2400 2.3582 1.8520 3.9240 0.0729 2.0813 1.6935 -0.0214 0.0000 -0.0135 -0.3913 0.258 - 22 13.9941 2.2087 1.6074 3.6371 0.0826 2.0612 1.6772 -0.0284 0.0000 -0.0057 -0.3805 0.253 - 23 14.6868 2.0715 1.3716 3.3240 0.0937 2.0104 1.6358 -0.0357 0.0000 0.0051 -0.3614 0.247 - 24 15.3105 1.9479 1.1479 2.9767 0.1055 1.9163 1.5593 -0.0422 0.0000 0.0175 -0.3330 0.239 - 25 15.8583 1.8393 0.9381 2.5856 0.1173 1.7641 1.4354 -0.0446 0.0000 0.0258 -0.2978 0.232 - 26 16.3244 1.7470 0.7427 2.1509 0.1299 1.5428 1.2553 -0.0287 0.0000 0.0168 -0.2659 0.237 - 27 16.6722 1.4928 0.4131 1.6906 0.1419 3.8542 1.1779 -0.1526 0.0000 0.0071 -0.1421 0.244 - 28 16.9098 1.1466 0.2292 1.2330 0.1550 3.7245 1.1383 -0.2546 0.0000 0.0585 -0.1115 0.199 - 29 17.0696 0.9138 0.1104 0.7514 0.1632 2.9343 0.8968 -0.3403 0.0000 0.0976 -0.0614 0.141 - 30 17.1499 0.7967 0.0322 0.2524 0.1668 1.2049 0.3682 -0.2561 0.0000 0.0560 -0.0154 0.098 + 1 0.0114 7.7520 0.3539 9.3353 0.2496 1.0677 0.8287 2.2283 0.0000 -0.1098 -0.3376 0.383 + 2 0.1025 7.6885 1.0491 7.6550 0.2494 1.2215 0.9480 0.3560 0.0000 -0.0963 -0.2842 0.352 + 3 0.2837 7.5620 1.7073 7.5196 0.2486 1.2488 0.9693 0.2289 0.0000 -0.0929 -0.2811 0.346 + 4 0.5530 7.3741 2.3052 7.4717 0.2460 1.2803 0.9937 0.1990 0.0000 -0.0876 -0.2808 0.338 + 5 0.9075 7.1267 2.8223 7.4271 0.2396 1.3204 1.0248 0.1892 0.0000 -0.0811 -0.2815 0.329 + 6 1.3432 6.8226 3.2414 7.3651 0.2234 1.3715 1.0645 0.1791 0.0000 -0.0741 -0.2836 0.320 + 7 1.8554 6.4651 3.5491 7.2658 0.1876 1.4341 1.1130 0.1591 0.0000 -0.0679 -0.2877 0.311 + 8 2.4386 6.0582 3.7368 7.1254 0.1526 1.5065 1.1692 0.1420 0.0000 -0.0629 -0.2945 0.304 + 9 3.0862 5.6062 3.8005 6.9419 0.1384 1.5928 1.2362 0.1194 0.0000 -0.0595 -0.3046 0.298 + 10 3.7613 5.1351 3.4440 6.7837 0.1262 1.7059 1.3239 0.0992 0.0000 -0.0554 -0.3184 0.292 + 11 4.4532 4.6522 3.3149 6.4484 0.1092 1.7956 1.3935 0.0791 0.0000 -0.0522 -0.3293 0.287 + 12 5.1831 4.1429 3.0930 6.1902 0.0820 1.9458 1.5101 0.0404 0.0000 -0.0527 -0.3520 0.285 + 13 6.0123 3.7903 3.4706 5.8853 0.0632 1.9317 1.5718 0.0281 0.0000 -0.0374 -0.3868 0.274 + 14 6.9353 3.6075 3.3775 5.6394 0.0609 1.9455 1.5830 0.0251 0.0000 -0.0328 -0.3852 0.271 + 15 7.8737 3.4215 3.2389 5.4079 0.0557 1.9682 1.6015 0.0197 0.0000 -0.0295 -0.3863 0.268 + 16 8.8172 3.2345 3.0619 5.1761 0.0525 1.9944 1.6228 0.0123 0.0000 -0.0270 -0.3886 0.267 + 17 9.7556 3.0486 2.8543 4.9395 0.0526 2.0208 1.6443 0.0058 0.0000 -0.0248 -0.3912 0.265 + 18 10.6786 2.8657 2.6239 4.6998 0.0551 2.0470 1.6656 -0.0011 0.0000 -0.0226 -0.3938 0.264 + 19 11.5760 2.6879 2.3787 4.4508 0.0593 2.0682 1.6829 -0.0079 0.0000 -0.0199 -0.3951 0.262 + 20 12.4328 2.5181 2.1010 4.1936 0.0652 2.0816 1.6938 -0.0150 0.0000 -0.0162 -0.3940 0.260 + 21 13.2400 2.3582 1.8520 3.9249 0.0729 2.0819 1.6940 -0.0216 0.0000 -0.0109 -0.3891 0.256 + 22 13.9941 2.2087 1.6074 3.6383 0.0825 2.0620 1.6778 -0.0288 0.0000 -0.0031 -0.3783 0.252 + 23 14.6868 2.0715 1.3716 3.3243 0.0937 2.0106 1.6360 -0.0359 0.0000 0.0077 -0.3591 0.245 + 24 15.3105 1.9479 1.1479 2.9762 0.1054 1.9161 1.5591 -0.0427 0.0000 0.0201 -0.3306 0.237 + 25 15.8583 1.8393 0.9381 2.5855 0.1172 1.7640 1.4354 -0.0449 0.0000 0.0284 -0.2955 0.230 + 26 16.3244 1.7470 0.7427 2.1499 0.1292 1.5421 1.2548 -0.0291 0.0000 0.0195 -0.2634 0.234 + 27 16.6722 1.4928 0.4131 1.6895 0.1413 3.8524 1.1773 -0.1535 0.0000 0.0091 -0.1411 0.242 + 28 16.9098 1.1466 0.2292 1.2323 0.1546 3.7228 1.1378 -0.2553 0.0000 0.0603 -0.1107 0.197 + 29 17.0696 0.9138 0.1104 0.7510 0.1630 2.9336 0.8965 -0.3412 0.0000 0.0988 -0.0609 0.140 + 30 17.1499 0.7967 0.0322 0.2524 0.1675 1.2055 0.3684 -0.2575 0.0000 0.0563 -0.0152 0.097 Surface # 2 main_wing (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 31 Surface area = 63.968842 Ave. chord = 3.715026 - CLsurf = 0.71192 Clsurf = 0.14451 - CYsurf = 0.03789 Cmsurf = -0.67775 - CDsurf = 0.04188 Cnsurf = 0.02286 - CDisurf = 0.04188 CDvsurf = 0.00000 + CLsurf = 0.71301 Clsurf = 0.14461 + CYsurf = 0.03792 Cmsurf = -0.67813 + CDsurf = 0.04192 Cnsurf = 0.02290 + CDisurf = 0.04192 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 1.39142 CDsurf = 0.08175 + CLsurf = 1.39354 CDsurf = 0.08183 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 31 -0.0114 7.7520 0.3539 9.3005 0.2502 1.0638 0.8256 2.2199 0.0000 -0.1072 0.3346 0.380 - 32 -0.1025 7.6885 1.0492 7.6342 0.2499 1.2182 0.9455 0.3550 0.0000 -0.0947 0.2823 0.350 - 33 -0.2837 7.5620 1.7073 7.5002 0.2488 1.2454 0.9666 0.2294 0.0000 -0.0913 0.2793 0.344 - 34 -0.5530 7.3741 2.3052 7.4544 0.2458 1.2761 0.9904 0.2038 0.0000 -0.0860 0.2790 0.337 - 35 -0.9075 7.1267 2.8223 7.4066 0.2392 1.3161 1.0214 0.1915 0.0000 -0.0793 0.2795 0.328 - 36 -1.3432 6.8226 3.2414 7.3342 0.2228 1.3675 1.0614 0.1707 0.0000 -0.0726 0.2814 0.318 - 37 -1.8554 6.4651 3.5491 7.2450 0.1867 1.4305 1.1102 0.1565 0.0000 -0.0662 0.2857 0.310 - 38 -2.4386 6.0582 3.7368 7.1072 0.1515 1.5021 1.1658 0.1438 0.0000 -0.0612 0.2925 0.303 - 39 -3.0862 5.6062 3.8005 6.9152 0.1366 1.5878 1.2323 0.1141 0.0000 -0.0581 0.3024 0.297 - 40 -3.7613 5.1351 3.4440 6.7218 0.1248 1.6879 1.3099 0.1089 0.0000 -0.0561 0.3164 0.293 - 41 -4.4532 4.6522 3.3149 6.4619 0.1092 1.8003 1.3972 0.0750 0.0000 -0.0561 0.3330 0.290 - 42 -5.1831 4.1429 3.0930 6.1886 0.0833 1.9448 1.5093 0.0426 0.0000 -0.0543 0.3532 0.286 - 43 -6.0123 3.7903 3.4706 5.8769 0.0638 1.9290 1.5696 0.0277 0.0000 -0.0395 0.3882 0.275 - 44 -6.9353 3.6075 3.3775 5.6338 0.0613 1.9435 1.5814 0.0253 0.0000 -0.0351 0.3869 0.272 - 45 -7.8737 3.4215 3.2389 5.4060 0.0559 1.9676 1.6010 0.0194 0.0000 -0.0318 0.3882 0.270 - 46 -8.8172 3.2345 3.0619 5.1745 0.0527 1.9938 1.6223 0.0124 0.0000 -0.0294 0.3906 0.268 - 47 -9.7556 3.0486 2.8543 4.9368 0.0527 2.0198 1.6434 0.0056 0.0000 -0.0274 0.3933 0.267 - 48 -10.6786 2.8657 2.6240 4.6983 0.0552 2.0463 1.6650 -0.0010 0.0000 -0.0251 0.3959 0.265 - 49 -11.5760 2.6879 2.3787 4.4492 0.0594 2.0675 1.6823 -0.0078 0.0000 -0.0225 0.3972 0.263 - 50 -12.4328 2.5181 2.1010 4.1923 0.0652 2.0809 1.6932 -0.0147 0.0000 -0.0188 0.3962 0.261 - 51 -13.2400 2.3582 1.8520 3.9239 0.0729 2.0813 1.6935 -0.0214 0.0000 -0.0135 0.3913 0.258 - 52 -13.9941 2.2087 1.6074 3.6370 0.0825 2.0612 1.6772 -0.0284 0.0000 -0.0057 0.3805 0.253 - 53 -14.6868 2.0715 1.3716 3.3240 0.0937 2.0103 1.6358 -0.0357 0.0000 0.0051 0.3614 0.247 - 54 -15.3105 1.9479 1.1479 2.9766 0.1054 1.9163 1.5592 -0.0422 0.0000 0.0175 0.3330 0.239 - 55 -15.8583 1.8393 0.9381 2.5856 0.1173 1.7640 1.4354 -0.0446 0.0000 0.0258 0.2978 0.232 - 56 -16.3244 1.7470 0.7427 2.1509 0.1299 1.5428 1.2553 -0.0287 0.0000 0.0168 0.2659 0.237 - 57 -16.6722 1.4928 0.4131 1.6906 0.1419 3.8541 1.1779 -0.1526 0.0000 0.0071 0.1421 0.244 - 58 -16.9098 1.1466 0.2292 1.2330 0.1550 3.7245 1.1383 -0.2546 0.0000 0.0585 0.1115 0.199 - 59 -17.0696 0.9138 0.1104 0.7514 0.1632 2.9343 0.8968 -0.3402 0.0000 0.0976 0.0614 0.141 - 60 -17.1499 0.7967 0.0322 0.2524 0.1668 1.2049 0.3682 -0.2561 0.0000 0.0560 0.0154 0.098 + 31 -0.0114 7.7520 0.3539 9.3353 0.2496 1.0677 0.8287 2.2283 0.0000 -0.1098 0.3376 0.383 + 32 -0.1025 7.6885 1.0491 7.6550 0.2494 1.2215 0.9480 0.3560 0.0000 -0.0963 0.2842 0.352 + 33 -0.2837 7.5620 1.7073 7.5196 0.2486 1.2488 0.9693 0.2289 0.0000 -0.0929 0.2811 0.346 + 34 -0.5530 7.3741 2.3052 7.4717 0.2460 1.2803 0.9937 0.1990 0.0000 -0.0876 0.2808 0.338 + 35 -0.9075 7.1267 2.8223 7.4271 0.2396 1.3204 1.0248 0.1892 0.0000 -0.0811 0.2815 0.329 + 36 -1.3432 6.8226 3.2414 7.3651 0.2234 1.3715 1.0645 0.1791 0.0000 -0.0741 0.2836 0.320 + 37 -1.8554 6.4651 3.5491 7.2658 0.1876 1.4341 1.1130 0.1591 0.0000 -0.0679 0.2877 0.311 + 38 -2.4386 6.0582 3.7368 7.1254 0.1526 1.5065 1.1692 0.1420 0.0000 -0.0629 0.2945 0.304 + 39 -3.0862 5.6062 3.8005 6.9419 0.1384 1.5928 1.2362 0.1194 0.0000 -0.0595 0.3046 0.298 + 40 -3.7613 5.1351 3.4440 6.7837 0.1262 1.7059 1.3239 0.0992 0.0000 -0.0554 0.3184 0.292 + 41 -4.4532 4.6522 3.3149 6.4484 0.1092 1.7956 1.3935 0.0791 0.0000 -0.0522 0.3293 0.287 + 42 -5.1831 4.1429 3.0930 6.1902 0.0820 1.9458 1.5101 0.0404 0.0000 -0.0527 0.3520 0.285 + 43 -6.0123 3.7903 3.4706 5.8853 0.0632 1.9317 1.5718 0.0281 0.0000 -0.0374 0.3868 0.274 + 44 -6.9353 3.6075 3.3775 5.6393 0.0609 1.9455 1.5830 0.0251 0.0000 -0.0327 0.3852 0.271 + 45 -7.8737 3.4215 3.2389 5.4079 0.0557 1.9682 1.6015 0.0197 0.0000 -0.0295 0.3863 0.268 + 46 -8.8172 3.2345 3.0619 5.1761 0.0525 1.9944 1.6228 0.0123 0.0000 -0.0270 0.3886 0.267 + 47 -9.7556 3.0486 2.8543 4.9395 0.0526 2.0208 1.6443 0.0058 0.0000 -0.0248 0.3912 0.265 + 48 -10.6786 2.8657 2.6239 4.6998 0.0551 2.0470 1.6656 -0.0011 0.0000 -0.0226 0.3938 0.264 + 49 -11.5760 2.6879 2.3787 4.4508 0.0593 2.0682 1.6829 -0.0079 0.0000 -0.0199 0.3951 0.262 + 50 -12.4328 2.5181 2.1010 4.1936 0.0652 2.0816 1.6938 -0.0150 0.0000 -0.0162 0.3940 0.260 + 51 -13.2400 2.3582 1.8520 3.9249 0.0729 2.0819 1.6940 -0.0216 0.0000 -0.0109 0.3891 0.256 + 52 -13.9941 2.2087 1.6074 3.6383 0.0825 2.0620 1.6778 -0.0288 0.0000 -0.0031 0.3783 0.252 + 53 -14.6868 2.0715 1.3716 3.3243 0.0937 2.0106 1.6360 -0.0359 0.0000 0.0077 0.3591 0.245 + 54 -15.3105 1.9479 1.1479 2.9762 0.1054 1.9161 1.5591 -0.0427 0.0000 0.0201 0.3306 0.237 + 55 -15.8583 1.8393 0.9381 2.5855 0.1172 1.7640 1.4354 -0.0449 0.0000 0.0284 0.2955 0.230 + 56 -16.3244 1.7470 0.7427 2.1498 0.1292 1.5421 1.2548 -0.0291 0.0000 0.0195 0.2634 0.234 + 57 -16.6722 1.4928 0.4131 1.6895 0.1413 3.8524 1.1773 -0.1535 0.0000 0.0091 0.1411 0.242 + 58 -16.9098 1.1466 0.2292 1.2323 0.1546 3.7228 1.1378 -0.2553 0.0000 0.0603 0.1107 0.197 + 59 -17.0696 0.9138 0.1104 0.7510 0.1630 2.9335 0.8965 -0.3412 0.0000 0.0988 0.0609 0.140 + 60 -17.1499 0.7967 0.0322 0.2524 0.1675 1.2055 0.3684 -0.2575 0.0000 0.0563 0.0152 0.097 Surface # 3 horizontal_stabilizer # Chordwise = 10 # Spanwise = 30 First strip = 61 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.07169 Clsurf = -0.00742 - CYsurf = -0.01220 Cmsurf = -0.35268 - CDsurf = 0.00876 Cnsurf = 0.00660 - CDisurf = 0.00876 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.07143 Clsurf = -0.00740 + CYsurf = -0.01215 Cmsurf = -0.35142 + CDsurf = 0.00873 Cnsurf = 0.00658 + CDisurf = 0.00873 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.43764 CDsurf = 0.05271 + CLsurf = 0.43605 CDsurf = 0.05253 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 61 0.0047 4.2713 0.0803 2.1369 0.1954 0.5626 0.4276 0.4544 0.0000 -0.0375 -0.1404 0.338 - 62 0.0418 4.2566 0.2392 1.5669 0.1960 0.4713 0.3582 0.0879 0.0000 -0.0309 -0.1070 0.336 - 63 0.1156 4.2274 0.3930 1.5221 0.1964 0.4666 0.3547 0.0615 0.0000 -0.0296 -0.1043 0.334 - 64 0.2254 4.1839 0.5386 1.5113 0.1958 0.4693 0.3568 0.0565 0.0000 -0.0279 -0.1031 0.328 - 65 0.3698 4.1268 0.6730 1.5039 0.1942 0.4740 0.3603 0.0550 0.0000 -0.0256 -0.1019 0.321 - 66 0.5474 4.0565 0.7936 1.5007 0.1912 0.4814 0.3660 0.0547 0.0000 -0.0228 -0.1008 0.312 - 67 0.7617 3.9717 0.9441 1.4960 0.1865 0.4906 0.3729 0.0540 0.0000 -0.0198 -0.0999 0.303 - 68 1.0116 3.8728 1.0344 1.4877 0.1798 0.5006 0.3805 0.0536 0.0000 -0.0170 -0.0992 0.295 - 69 1.2891 3.7630 1.1046 1.4780 0.1715 0.5122 0.3893 0.0534 0.0000 -0.0144 -0.0989 0.287 - 70 1.5912 3.6435 1.1542 1.4675 0.1621 0.5256 0.3995 0.0533 0.0000 -0.0119 -0.0991 0.280 - 71 1.9146 3.5155 1.1831 1.4529 0.1527 0.5396 0.4102 0.0533 0.0000 -0.0097 -0.0996 0.274 - 72 2.2558 3.3805 1.1921 1.4372 0.1446 0.5554 0.4222 0.0534 0.0000 -0.0077 -0.1006 0.268 - 73 2.6109 3.2400 1.1821 1.4198 0.1383 0.5728 0.4354 0.0537 0.0000 -0.0058 -0.1019 0.263 - 74 2.9762 3.0955 1.1548 1.4005 0.1340 0.5918 0.4498 0.0540 0.0000 -0.0040 -0.1035 0.259 - 75 3.3476 2.9485 1.1122 1.3781 0.1312 0.6117 0.4650 0.0542 0.0000 -0.0020 -0.1052 0.254 - 76 3.7210 2.8008 1.0564 1.3530 0.1297 0.6326 0.4808 0.0544 0.0000 0.0000 -0.1069 0.250 - 77 4.0924 2.6538 0.9900 1.3232 0.1291 0.6534 0.4966 0.0543 0.0000 0.0024 -0.1084 0.245 - 78 4.4577 2.5093 0.9155 1.2879 0.1295 0.6731 0.5116 0.0539 0.0000 0.0052 -0.1093 0.240 - 79 4.8128 2.3687 0.8353 1.2448 0.1306 0.6896 0.5242 0.0529 0.0000 0.0085 -0.1093 0.234 - 80 5.1540 2.2338 0.7518 1.1949 0.1324 0.7026 0.5340 0.0515 0.0000 0.0125 -0.1080 0.227 - 81 5.4774 2.1058 0.6671 1.1358 0.1346 0.7090 0.5389 0.0492 0.0000 0.0174 -0.1050 0.218 - 82 5.7795 1.9862 0.5830 1.0664 0.1372 0.7065 0.5370 0.0460 0.0000 0.0230 -0.0997 0.207 - 83 6.0570 1.8764 0.5012 0.9857 0.1399 0.6920 0.5260 0.0418 0.0000 0.0290 -0.0922 0.195 - 84 6.3069 1.7776 0.4225 0.8954 0.1424 0.6643 0.5050 0.0367 0.0000 0.0352 -0.0823 0.180 - 85 6.5264 1.6907 0.3478 0.7946 0.1447 0.6208 0.4719 0.0301 0.0000 0.0406 -0.0703 0.164 - 86 6.7314 1.6096 0.3326 0.6784 0.1468 0.5577 0.4239 0.0229 0.0000 0.0442 -0.0566 0.146 - 87 6.9144 1.5372 0.2507 0.5426 0.1487 0.4683 0.3559 0.0141 0.0000 0.0444 -0.0413 0.125 - 88 7.0535 1.4822 0.1746 0.3950 0.1501 0.3549 0.2697 0.0049 0.0000 0.0388 -0.0268 0.106 - 89 7.1471 1.4451 0.1029 0.2400 0.1510 0.2224 0.1690 -0.0023 0.0000 0.0268 -0.0145 0.091 - 90 7.1941 1.4265 0.0340 0.0806 0.1515 0.0776 0.0590 -0.0093 0.0000 0.0096 -0.0046 0.088 + 61 0.0047 4.2713 0.0803 2.1247 0.1955 0.5596 0.4254 0.4504 0.0000 -0.0374 -0.1397 0.338 + 62 0.0418 4.2566 0.2392 1.5596 0.1962 0.4691 0.3566 0.0874 0.0000 -0.0308 -0.1065 0.336 + 63 0.1156 4.2274 0.3930 1.5141 0.1965 0.4642 0.3528 0.0612 0.0000 -0.0296 -0.1038 0.334 + 64 0.2254 4.1839 0.5386 1.5040 0.1960 0.4672 0.3551 0.0558 0.0000 -0.0278 -0.1026 0.328 + 65 0.3698 4.1268 0.6730 1.4982 0.1943 0.4722 0.3589 0.0547 0.0000 -0.0254 -0.1015 0.321 + 66 0.5474 4.0565 0.7936 1.4944 0.1913 0.4795 0.3645 0.0542 0.0000 -0.0227 -0.1004 0.312 + 67 0.7617 3.9717 0.9441 1.4894 0.1866 0.4884 0.3712 0.0538 0.0000 -0.0198 -0.0995 0.303 + 68 1.0116 3.8728 1.0344 1.4804 0.1799 0.4982 0.3787 0.0532 0.0000 -0.0169 -0.0987 0.295 + 69 1.2891 3.7630 1.1046 1.4711 0.1716 0.5099 0.3875 0.0530 0.0000 -0.0143 -0.0985 0.287 + 70 1.5912 3.6435 1.1542 1.4598 0.1622 0.5228 0.3974 0.0532 0.0000 -0.0119 -0.0986 0.280 + 71 1.9146 3.5155 1.1831 1.4468 0.1529 0.5373 0.4084 0.0533 0.0000 -0.0097 -0.0992 0.274 + 72 2.2558 3.3805 1.1921 1.4309 0.1447 0.5530 0.4204 0.0531 0.0000 -0.0077 -0.1002 0.268 + 73 2.6109 3.2400 1.1821 1.4138 0.1385 0.5704 0.4336 0.0535 0.0000 -0.0058 -0.1015 0.263 + 74 2.9762 3.0955 1.1548 1.3956 0.1341 0.5897 0.4482 0.0540 0.0000 -0.0040 -0.1032 0.259 + 75 3.3476 2.9485 1.1122 1.3730 0.1313 0.6094 0.4632 0.0541 0.0000 -0.0021 -0.1049 0.255 + 76 3.7210 2.8008 1.0564 1.3477 0.1298 0.6301 0.4789 0.0543 0.0000 -0.0000 -0.1066 0.250 + 77 4.0924 2.6538 0.9900 1.3184 0.1292 0.6510 0.4948 0.0542 0.0000 0.0023 -0.1081 0.245 + 78 4.4577 2.5093 0.9155 1.2836 0.1295 0.6709 0.5099 0.0535 0.0000 0.0051 -0.1090 0.240 + 79 4.8128 2.3687 0.8353 1.2417 0.1306 0.6879 0.5229 0.0528 0.0000 0.0085 -0.1090 0.234 + 80 5.1540 2.2338 0.7518 1.1922 0.1324 0.7009 0.5328 0.0516 0.0000 0.0124 -0.1078 0.227 + 81 5.4774 2.1058 0.6671 1.1333 0.1347 0.7074 0.5377 0.0492 0.0000 0.0173 -0.1048 0.218 + 82 5.7795 1.9862 0.5830 1.0634 0.1372 0.7045 0.5355 0.0458 0.0000 0.0229 -0.0995 0.207 + 83 6.0570 1.8764 0.5012 0.9838 0.1399 0.6906 0.5250 0.0417 0.0000 0.0290 -0.0919 0.195 + 84 6.3069 1.7776 0.4225 0.8939 0.1424 0.6632 0.5041 0.0366 0.0000 0.0352 -0.0821 0.180 + 85 6.5264 1.6907 0.3478 0.7935 0.1447 0.6199 0.4712 0.0302 0.0000 0.0405 -0.0702 0.164 + 86 6.7314 1.6096 0.3326 0.6777 0.1468 0.5571 0.4234 0.0230 0.0000 0.0442 -0.0565 0.146 + 87 6.9144 1.5372 0.2507 0.5420 0.1487 0.4677 0.3554 0.0143 0.0000 0.0444 -0.0412 0.125 + 88 7.0535 1.4822 0.1746 0.3945 0.1501 0.3544 0.2693 0.0049 0.0000 0.0387 -0.0267 0.106 + 89 7.1471 1.4451 0.1029 0.2398 0.1510 0.2222 0.1689 -0.0023 0.0000 0.0268 -0.0145 0.091 + 90 7.1941 1.4265 0.0340 0.0805 0.1515 0.0775 0.0589 -0.0092 0.0000 0.0096 -0.0045 0.088 Surface # 4 horizontal_stabilizer (YDUP) # Chordwise = 10 # Spanwise = 30 First strip = 91 - Surface area = 20.744608 Ave. chord = 2.848572 - CLsurf = 0.07169 Clsurf = 0.00742 - CYsurf = 0.01220 Cmsurf = -0.35267 - CDsurf = 0.00876 Cnsurf = -0.00660 - CDisurf = 0.00876 CDvsurf = 0.00000 + Surface area = 20.744604 Ave. chord = 2.848572 + CLsurf = 0.07143 Clsurf = 0.00740 + CYsurf = 0.01215 Cmsurf = -0.35141 + CDsurf = 0.00873 Cnsurf = -0.00658 + CDisurf = 0.00873 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.43763 CDsurf = 0.05271 + CLsurf = 0.43605 CDsurf = 0.05253 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 91 -0.0047 4.2713 0.0803 2.1369 0.1954 0.5626 0.4276 0.4544 0.0000 -0.0375 0.1404 0.338 - 92 -0.0418 4.2566 0.2392 1.5669 0.1961 0.4713 0.3582 0.0879 0.0000 -0.0309 0.1070 0.336 - 93 -0.1156 4.2274 0.3930 1.5221 0.1964 0.4666 0.3547 0.0615 0.0000 -0.0296 0.1043 0.334 - 94 -0.2254 4.1839 0.5386 1.5113 0.1958 0.4693 0.3568 0.0565 0.0000 -0.0279 0.1031 0.328 - 95 -0.3698 4.1268 0.6730 1.5039 0.1942 0.4740 0.3603 0.0550 0.0000 -0.0256 0.1019 0.321 - 96 -0.5474 4.0565 0.7936 1.5007 0.1912 0.4814 0.3659 0.0547 0.0000 -0.0228 0.1008 0.312 - 97 -0.7617 3.9717 0.9441 1.4960 0.1865 0.4906 0.3729 0.0540 0.0000 -0.0198 0.0999 0.303 - 98 -1.0116 3.8728 1.0344 1.4877 0.1798 0.5006 0.3805 0.0536 0.0000 -0.0170 0.0992 0.295 - 99 -1.2891 3.7630 1.1046 1.4780 0.1715 0.5122 0.3893 0.0534 0.0000 -0.0144 0.0989 0.287 - 100 -1.5912 3.6435 1.1542 1.4675 0.1621 0.5256 0.3995 0.0533 0.0000 -0.0119 0.0991 0.280 - 101 -1.9146 3.5155 1.1831 1.4528 0.1527 0.5396 0.4102 0.0533 0.0000 -0.0097 0.0996 0.274 - 102 -2.2558 3.3805 1.1921 1.4371 0.1446 0.5554 0.4222 0.0534 0.0000 -0.0077 0.1006 0.268 - 103 -2.6109 3.2400 1.1821 1.4197 0.1383 0.5728 0.4354 0.0537 0.0000 -0.0058 0.1019 0.263 - 104 -2.9762 3.0955 1.1548 1.4005 0.1340 0.5918 0.4498 0.0540 0.0000 -0.0040 0.1035 0.259 - 105 -3.3476 2.9485 1.1122 1.3781 0.1312 0.6117 0.4649 0.0542 0.0000 -0.0020 0.1052 0.254 - 106 -3.7210 2.8008 1.0564 1.3529 0.1297 0.6326 0.4808 0.0544 0.0000 0.0000 0.1069 0.250 - 107 -4.0924 2.6538 0.9900 1.3231 0.1291 0.6533 0.4966 0.0543 0.0000 0.0024 0.1084 0.245 - 108 -4.4577 2.5093 0.9155 1.2879 0.1295 0.6731 0.5116 0.0539 0.0000 0.0052 0.1093 0.240 - 109 -4.8128 2.3687 0.8353 1.2447 0.1306 0.6896 0.5242 0.0529 0.0000 0.0085 0.1093 0.234 - 110 -5.1540 2.2338 0.7518 1.1949 0.1324 0.7025 0.5340 0.0515 0.0000 0.0125 0.1080 0.227 - 111 -5.4774 2.1058 0.6671 1.1358 0.1346 0.7090 0.5389 0.0492 0.0000 0.0174 0.1050 0.218 - 112 -5.7795 1.9862 0.5830 1.0664 0.1372 0.7064 0.5370 0.0460 0.0000 0.0230 0.0997 0.207 - 113 -6.0570 1.8764 0.5012 0.9857 0.1399 0.6920 0.5259 0.0418 0.0000 0.0290 0.0922 0.195 - 114 -6.3069 1.7776 0.4225 0.8954 0.1424 0.6643 0.5049 0.0367 0.0000 0.0352 0.0822 0.180 - 115 -6.5264 1.6907 0.3478 0.7946 0.1447 0.6208 0.4719 0.0301 0.0000 0.0406 0.0703 0.164 - 116 -6.7314 1.6096 0.3326 0.6784 0.1468 0.5577 0.4239 0.0229 0.0000 0.0442 0.0566 0.146 - 117 -6.9144 1.5372 0.2507 0.5426 0.1487 0.4682 0.3559 0.0141 0.0000 0.0444 0.0413 0.125 - 118 -7.0535 1.4822 0.1746 0.3950 0.1501 0.3549 0.2697 0.0049 0.0000 0.0388 0.0268 0.106 - 119 -7.1471 1.4451 0.1029 0.2400 0.1510 0.2224 0.1690 -0.0023 0.0000 0.0268 0.0145 0.091 - 120 -7.1941 1.4265 0.0340 0.0806 0.1515 0.0776 0.0590 -0.0093 0.0000 0.0096 0.0046 0.088 + 91 -0.0047 4.2713 0.0803 2.1247 0.1955 0.5596 0.4254 0.4504 0.0000 -0.0374 0.1397 0.338 + 92 -0.0418 4.2566 0.2392 1.5596 0.1962 0.4691 0.3566 0.0874 0.0000 -0.0308 0.1065 0.336 + 93 -0.1156 4.2274 0.3930 1.5141 0.1965 0.4642 0.3528 0.0612 0.0000 -0.0296 0.1038 0.334 + 94 -0.2254 4.1839 0.5386 1.5040 0.1960 0.4672 0.3551 0.0558 0.0000 -0.0278 0.1026 0.328 + 95 -0.3698 4.1268 0.6730 1.4982 0.1943 0.4722 0.3589 0.0547 0.0000 -0.0254 0.1015 0.321 + 96 -0.5474 4.0565 0.7936 1.4944 0.1913 0.4795 0.3645 0.0542 0.0000 -0.0227 0.1004 0.312 + 97 -0.7617 3.9717 0.9441 1.4894 0.1866 0.4884 0.3712 0.0538 0.0000 -0.0198 0.0995 0.303 + 98 -1.0116 3.8728 1.0344 1.4804 0.1799 0.4982 0.3787 0.0532 0.0000 -0.0169 0.0987 0.295 + 99 -1.2891 3.7630 1.1046 1.4711 0.1716 0.5098 0.3875 0.0530 0.0000 -0.0143 0.0985 0.287 + 100 -1.5912 3.6435 1.1542 1.4598 0.1622 0.5228 0.3974 0.0532 0.0000 -0.0119 0.0986 0.280 + 101 -1.9146 3.5155 1.1831 1.4468 0.1529 0.5373 0.4084 0.0533 0.0000 -0.0097 0.0992 0.274 + 102 -2.2558 3.3805 1.1921 1.4309 0.1447 0.5530 0.4204 0.0531 0.0000 -0.0077 0.1002 0.268 + 103 -2.6109 3.2400 1.1821 1.4138 0.1385 0.5704 0.4336 0.0535 0.0000 -0.0058 0.1015 0.263 + 104 -2.9762 3.0955 1.1548 1.3956 0.1341 0.5897 0.4482 0.0540 0.0000 -0.0040 0.1032 0.259 + 105 -3.3476 2.9485 1.1122 1.3730 0.1313 0.6094 0.4632 0.0541 0.0000 -0.0021 0.1049 0.255 + 106 -3.7210 2.8008 1.0564 1.3477 0.1298 0.6301 0.4789 0.0543 0.0000 -0.0000 0.1066 0.250 + 107 -4.0924 2.6538 0.9900 1.3184 0.1292 0.6510 0.4948 0.0542 0.0000 0.0023 0.1081 0.245 + 108 -4.4577 2.5093 0.9155 1.2836 0.1295 0.6709 0.5099 0.0535 0.0000 0.0051 0.1090 0.240 + 109 -4.8128 2.3687 0.8353 1.2417 0.1306 0.6879 0.5229 0.0528 0.0000 0.0085 0.1090 0.234 + 110 -5.1540 2.2338 0.7518 1.1922 0.1324 0.7009 0.5328 0.0516 0.0000 0.0124 0.1078 0.227 + 111 -5.4774 2.1058 0.6671 1.1333 0.1347 0.7074 0.5377 0.0492 0.0000 0.0173 0.1048 0.218 + 112 -5.7795 1.9862 0.5830 1.0634 0.1372 0.7045 0.5355 0.0458 0.0000 0.0229 0.0995 0.207 + 113 -6.0570 1.8764 0.5012 0.9838 0.1399 0.6906 0.5250 0.0417 0.0000 0.0290 0.0919 0.195 + 114 -6.3069 1.7776 0.4225 0.8939 0.1424 0.6632 0.5041 0.0366 0.0000 0.0352 0.0821 0.180 + 115 -6.5264 1.6907 0.3478 0.7935 0.1447 0.6199 0.4712 0.0302 0.0000 0.0405 0.0702 0.164 + 116 -6.7314 1.6096 0.3326 0.6777 0.1468 0.5571 0.4234 0.0230 0.0000 0.0442 0.0565 0.146 + 117 -6.9144 1.5372 0.2507 0.5420 0.1487 0.4677 0.3554 0.0143 0.0000 0.0444 0.0412 0.125 + 118 -7.0535 1.4822 0.1746 0.3945 0.1501 0.3544 0.2693 0.0049 0.0000 0.0387 0.0267 0.106 + 119 -7.1471 1.4451 0.1029 0.2398 0.1510 0.2222 0.1689 -0.0023 0.0000 0.0268 0.0145 0.091 + 120 -7.1941 1.4265 0.0340 0.0805 0.1515 0.0775 0.0589 -0.0092 0.0000 0.0096 0.0045 0.088 Surface # 5 vertical_stabilizer # Chordwise = 10 # Spanwise = 30 First strip =121 - Surface area = 34.910366 Ave. chord = 4.190920 + Surface area = 34.910358 Ave. chord = 4.190919 CLsurf = 0.00000 Clsurf = 0.00000 CYsurf = 0.00000 Cmsurf = -0.00000 CDsurf = -0.00000 Cnsurf = -0.00000 @@ -198,61 +198,61 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.478 - 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.487 - 123 0.0000 9.5266 1.4857 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.498 - 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.507 - 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.513 - 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.512 - 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.504 - 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.485 - 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.452 - 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.405 - 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.360 - 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.340 - 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.323 - 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.307 - 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.291 + 121 0.0000 10.0347 0.6931 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.510 + 122 0.0000 9.8296 1.1101 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.511 + 123 0.0000 9.5266 1.4857 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.525 + 124 0.0000 9.1281 1.8040 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.534 + 125 0.0000 8.6377 2.0517 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.537 + 126 0.0000 8.0598 2.2181 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.530 + 127 0.0000 7.4000 2.2957 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.520 + 128 0.0000 6.6646 2.2808 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.496 + 129 0.0000 5.8609 2.1733 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.462 + 130 0.0000 4.9969 1.9773 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.410 + 131 0.0000 4.4389 1.6667 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.363 + 132 0.0000 4.2198 1.6478 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.342 + 133 0.0000 3.9932 1.6033 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.329 + 134 0.0000 3.7615 1.5362 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.312 + 135 0.0000 3.5271 1.4499 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.297 136 0.0000 3.2923 1.3482 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.279 - 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.267 + 137 0.0000 3.0597 1.2352 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.266 138 0.0000 2.8315 1.1147 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.256 - 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.243 - 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.235 - 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.227 - 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.215 + 139 0.0000 2.6103 0.9908 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.248 + 140 0.0000 2.3983 0.8670 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.237 + 141 0.0000 2.1977 0.7464 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.226 + 142 0.0000 2.0106 0.6318 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.213 143 0.0000 1.8390 0.5251 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.200 144 0.0000 1.6847 0.4276 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.184 - 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.166 + 145 0.0000 1.5493 0.3400 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.165 146 0.0000 1.4342 0.2622 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.144 - 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.120 - 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.098 - 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.081 - 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.073 + 147 0.0000 1.3407 0.1933 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.123 + 148 0.0000 1.2696 0.1322 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.100 + 149 0.0000 1.2218 0.0769 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.082 + 150 0.0000 1.1978 0.0252 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.075 Surface # 6 fuselage_horizontal # Chordwise = 10 # Spanwise = 10 First strip =151 Surface area = 123.841202 Ave. chord = 33.112617 - CLsurf = 0.01614 Clsurf = 0.00000 - CYsurf = -0.00000 Cmsurf = 0.08794 - CDsurf = -0.00005 Cnsurf = -0.00000 + CLsurf = 0.01607 Clsurf = -0.00000 + CYsurf = 0.00000 Cmsurf = 0.08801 + CDsurf = -0.00005 Cnsurf = 0.00000 CDisurf = -0.00005 CDvsurf = 0.00000 Forces referred to Ssurf, Cave about hinge axis thru LE - CLsurf = 0.01628 CDsurf = -0.00005 + CLsurf = 0.01621 CDsurf = -0.00005 Deflect = Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 151 -1.6830 26.5957 9.9468 0.3734 0.2810 0.1438 0.0154 -0.0065 0.0000 0.0054 0.0002 -0.098 - 152 -1.3090 31.2096 11.6724 0.5269 0.3023 0.0627 0.0175 -0.0019 0.0000 0.0071 0.0007 -0.157 - 153 -0.9350 34.0626 12.7394 0.5606 0.2679 0.0391 0.0167 0.0002 0.0000 0.0092 0.0017 -0.302 - 154 -0.5610 36.1619 13.5246 0.5864 0.2590 0.0266 0.0162 0.0017 0.0000 0.0101 0.0027 -0.373 - 155 -0.1870 37.5332 14.0374 0.6051 0.2601 0.0181 0.0156 0.0042 0.0000 0.0103 0.0043 -0.407 - 156 0.1870 37.5332 14.0374 0.6051 0.2601 0.0181 0.0156 0.0042 0.0000 0.0103 0.0043 -0.407 - 157 0.5610 36.1619 13.5246 0.5864 0.2590 0.0266 0.0162 0.0017 0.0000 0.0101 0.0027 -0.373 - 158 0.9350 34.0626 12.7394 0.5606 0.2679 0.0391 0.0167 0.0002 0.0000 0.0092 0.0017 -0.302 - 159 1.3090 31.2096 11.6724 0.5269 0.3024 0.0627 0.0175 -0.0019 0.0000 0.0071 0.0007 -0.157 - 160 1.6830 26.5957 9.9468 0.3734 0.2810 0.1438 0.0154 -0.0065 0.0000 0.0054 0.0002 -0.098 + 151 -1.6830 26.5957 9.9468 0.3715 0.2810 0.1431 0.0153 -0.0065 0.0000 0.0054 0.0003 -0.102 + 152 -1.3090 31.2096 11.6724 0.5243 0.3023 0.0624 0.0174 -0.0019 0.0000 0.0071 0.0007 -0.160 + 153 -0.9350 34.0626 12.7394 0.5581 0.2680 0.0389 0.0166 0.0001 0.0000 0.0092 0.0017 -0.305 + 154 -0.5610 36.1619 13.5246 0.5841 0.2592 0.0265 0.0161 0.0016 0.0000 0.0101 0.0027 -0.377 + 155 -0.1870 37.5332 14.0374 0.6029 0.2603 0.0180 0.0156 0.0042 0.0000 0.0103 0.0043 -0.411 + 156 0.1870 37.5332 14.0374 0.6029 0.2603 0.0180 0.0156 0.0042 0.0000 0.0103 0.0043 -0.411 + 157 0.5610 36.1619 13.5246 0.5841 0.2592 0.0265 0.0161 0.0016 0.0000 0.0101 0.0027 -0.377 + 158 0.9350 34.0626 12.7394 0.5581 0.2680 0.0389 0.0166 0.0001 0.0000 0.0092 0.0017 -0.305 + 159 1.3090 31.2096 11.6724 0.5243 0.3023 0.0624 0.0174 -0.0019 0.0000 0.0071 0.0007 -0.160 + 160 1.6830 26.5957 9.9468 0.3715 0.2810 0.1431 0.0153 -0.0065 0.0000 0.0054 0.0003 -0.102 Surface # 7 fuselage_vertical # Chordwise = 10 # Spanwise = 10 First strip =161 @@ -268,14 +268,14 @@ Strip Forces referred to Strip Area, Chord j Yle Chord Area c cl ai cl_norm cl cd cdv cm_c/4 cm_LE C.P.x/c - 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.616 + 161 0.0000 26.5957 9.9468 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 1.363 162 0.0000 31.2096 11.6724 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 163 0.0000 34.0626 12.7394 -0.0000 0.0003 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 164 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 - 165 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 - 166 0.0000 37.5332 14.0374 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.036 - 167 0.0000 36.1619 13.5246 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.377 - 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.555 - 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.680 - 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.776 + 163 0.0000 34.0626 12.7394 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 164 0.0000 36.1619 13.5246 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 + 165 0.0000 37.5332 14.0374 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 + 166 0.0000 37.5332 14.0374 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 + 167 0.0000 36.1619 13.5246 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.060 + 168 0.0000 34.0626 12.7394 -0.0000 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.408 + 169 0.0000 31.2096 11.6724 -0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.624 + 170 0.0000 26.5957 9.9468 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 0.0000 0.0000 0.759 --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_01_01.txt b/regression/scripts/AVL/avl_files/surface_forces_case_01_01.txt index dea8a6ee7f..c926e35eb0 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_01_01.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_01_01.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0086 0.0004 0.0040 0.0001 -0.0002 0.0026 0.0004 0.0000 main_wing - 2 63.969 0.0086 0.0004 0.0040 -0.0001 0.0002 -0.0026 0.0004 0.0000 main_wing (YDUP) - 3 20.745 -0.0277 0.0001 0.1330 0.0045 -0.0027 0.0027 0.0001 0.0000 horizontal_stabilizer - 4 20.745 -0.0277 0.0001 0.1330 -0.0045 0.0027 -0.0027 0.0001 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.0092 0.0004 0.0036 0.0001 -0.0002 0.0025 0.0004 0.0000 main_wing + 2 63.969 0.0092 0.0004 0.0036 -0.0001 0.0002 -0.0025 0.0004 0.0000 main_wing (YDUP) + 3 20.745 -0.0279 0.0001 0.1337 0.0045 -0.0028 0.0027 0.0001 0.0000 horizontal_stabilizer + 4 20.745 -0.0279 0.0001 0.1337 -0.0045 0.0028 -0.0027 0.0001 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0097 0.0002 -0.0240 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal + 6 123.841 -0.0098 0.0002 -0.0239 -0.0000 -0.0000 0.0000 0.0002 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.0167 0.0007 0.0000 0.0000 main_wing - 2 63.969 3.715 0.0167 0.0007 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.1691 0.0006 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.1691 0.0006 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.0179 0.0007 0.0000 0.0000 main_wing + 2 63.969 3.715 0.0179 0.0007 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.1699 0.0006 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.1699 0.0006 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0098 0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 -0.0099 0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_01_02.txt b/regression/scripts/AVL/avl_files/surface_forces_case_01_02.txt index 5c46170821..a3efb26f05 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_01_02.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_01_02.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0900 0.0012 -0.0716 -0.0061 0.0007 -0.0143 0.0012 0.0000 main_wing - 2 63.969 0.0900 0.0012 -0.0716 0.0061 -0.0007 0.0143 0.0012 0.0000 main_wing (YDUP) - 3 20.745 -0.0124 -0.0002 0.0590 0.0020 -0.0012 0.0011 -0.0002 0.0000 horizontal_stabilizer - 4 20.745 -0.0124 -0.0002 0.0590 -0.0020 0.0012 -0.0011 -0.0002 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0051 0.0000 -0.0036 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 1 63.969 0.0906 0.0012 -0.0719 -0.0061 0.0007 -0.0143 0.0012 0.0000 main_wing + 2 63.969 0.0906 0.0012 -0.0719 0.0061 -0.0007 0.0143 0.0012 0.0000 main_wing (YDUP) + 3 20.745 -0.0125 -0.0002 0.0596 0.0020 -0.0012 0.0011 -0.0002 0.0000 horizontal_stabilizer + 4 20.745 -0.0125 -0.0002 0.0596 -0.0020 0.0012 -0.0011 -0.0002 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer + 6 123.841 -0.0051 0.0000 -0.0035 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal + 7 123.841 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.1761 0.0024 0.0000 0.0000 main_wing - 2 63.969 3.715 0.1761 0.0024 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.0753 -0.0011 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.0753 -0.0011 0.0000 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0051 0.0000 0.0000 0.0000 fuselage_horizontal + 1 63.969 3.715 0.1773 0.0023 0.0000 0.0000 main_wing + 2 63.969 3.715 0.1773 0.0023 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.0761 -0.0011 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.0761 -0.0011 0.0000 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer + 6 123.841 33.113 -0.0052 0.0000 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_01_03.txt b/regression/scripts/AVL/avl_files/surface_forces_case_01_03.txt index 450d322959..8d3a07afb1 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_01_03.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_01_03.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.1713 0.0031 -0.1472 -0.0114 0.0002 -0.0311 0.0031 0.0000 main_wing - 2 63.969 0.1713 0.0031 -0.1472 0.0114 -0.0002 0.0311 0.0031 0.0000 main_wing (YDUP) - 3 20.745 0.0031 0.0001 -0.0157 -0.0005 0.0003 -0.0005 0.0001 0.0000 horizontal_stabilizer - 4 20.745 0.0031 0.0001 -0.0157 0.0005 -0.0003 0.0005 0.0001 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.1719 0.0030 -0.1475 -0.0113 0.0002 -0.0312 0.0030 0.0000 main_wing + 2 63.969 0.1719 0.0030 -0.1475 0.0113 -0.0002 0.0312 0.0030 0.0000 main_wing (YDUP) + 3 20.745 0.0030 0.0001 -0.0151 -0.0005 0.0003 -0.0005 0.0001 0.0000 horizontal_stabilizer + 4 20.745 0.0030 0.0001 -0.0151 0.0005 -0.0003 0.0005 0.0001 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0004 -0.0001 0.0168 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal - 7 123.841 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 6 123.841 -0.0005 -0.0001 0.0169 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.3352 0.0061 0.0000 0.0000 main_wing - 2 63.969 3.715 0.3352 0.0061 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.0188 0.0005 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.0188 0.0005 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.3363 0.0059 0.0000 0.0000 main_wing + 2 63.969 3.715 0.3363 0.0059 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.0180 0.0005 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.0180 0.0005 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 -0.0005 -0.0001 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_01_04.txt b/regression/scripts/AVL/avl_files/surface_forces_case_01_04.txt index e8fae34876..7f8cfc5d80 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_01_04.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_01_04.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.2927 0.0079 -0.2597 -0.0174 -0.0030 -0.0561 0.0079 0.0000 main_wing - 2 63.969 0.2927 0.0079 -0.2597 0.0174 0.0030 0.0561 0.0079 0.0000 main_wing (YDUP) - 3 20.745 0.0262 0.0015 -0.1283 -0.0042 0.0024 -0.0028 0.0015 0.0000 horizontal_stabilizer - 4 20.745 0.0262 0.0015 -0.1283 0.0042 -0.0024 0.0028 0.0015 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.2933 0.0077 -0.2601 -0.0173 -0.0031 -0.0561 0.0077 0.0000 main_wing + 2 63.969 0.2933 0.0077 -0.2601 0.0173 0.0031 0.0561 0.0077 0.0000 main_wing (YDUP) + 3 20.745 0.0261 0.0015 -0.1277 -0.0041 0.0023 -0.0028 0.0015 0.0000 horizontal_stabilizer + 4 20.745 0.0261 0.0015 -0.1277 0.0041 -0.0023 0.0028 0.0015 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0064 -0.0002 0.0470 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 6 123.841 0.0063 -0.0002 0.0470 -0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.5722 0.0154 0.0000 0.0000 main_wing - 2 63.969 3.715 0.5722 0.0154 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.1598 0.0090 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.1598 0.0090 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.5734 0.0150 0.0000 0.0000 main_wing + 2 63.969 3.715 0.5734 0.0150 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.1590 0.0090 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.1590 0.0090 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0065 -0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0064 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_01_05.txt b/regression/scripts/AVL/avl_files/surface_forces_case_01_05.txt index 54388ddd95..f80611df85 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_01_05.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_01_05.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.3728 0.0124 -0.3336 -0.0202 -0.0069 -0.0724 0.0124 0.0000 main_wing - 2 63.969 0.3728 0.0124 -0.3336 0.0202 0.0069 0.0724 0.0124 0.0000 main_wing (YDUP) - 3 20.745 0.0415 0.0031 -0.2032 -0.0066 0.0036 -0.0043 0.0031 0.0000 horizontal_stabilizer - 4 20.745 0.0415 0.0031 -0.2031 0.0066 -0.0036 0.0043 0.0031 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.3735 0.0120 -0.3340 -0.0200 -0.0069 -0.0724 0.0120 0.0000 main_wing + 2 63.969 0.3735 0.0120 -0.3340 0.0200 0.0069 0.0724 0.0120 0.0000 main_wing (YDUP) + 3 20.745 0.0414 0.0031 -0.2025 -0.0065 0.0036 -0.0043 0.0031 0.0000 horizontal_stabilizer + 4 20.745 0.0414 0.0031 -0.2025 0.0065 -0.0036 0.0043 0.0031 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0109 -0.0002 0.0667 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0108 -0.0003 0.0668 0.0000 -0.0000 0.0000 -0.0003 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.7287 0.0242 0.0000 0.0000 main_wing - 2 63.969 3.715 0.7287 0.0242 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.2530 0.0187 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.2530 0.0187 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.7299 0.0234 0.0000 0.0000 main_wing + 2 63.969 3.715 0.7299 0.0234 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.2522 0.0186 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.2522 0.0186 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0110 -0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0109 -0.0003 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_01_06.txt b/regression/scripts/AVL/avl_files/surface_forces_case_01_06.txt index dba55a3de9..fe503d4c66 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_01_06.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_01_06.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.4914 0.0209 -0.4420 -0.0224 -0.0150 -0.0962 0.0209 0.0000 main_wing - 2 63.969 0.4914 0.0209 -0.4420 0.0224 0.0150 0.0962 0.0209 0.0000 main_wing (YDUP) - 3 20.745 0.0640 0.0065 -0.3143 -0.0101 0.0053 -0.0066 0.0065 0.0000 horizontal_stabilizer - 4 20.745 0.0640 0.0065 -0.3143 0.0101 -0.0053 0.0066 0.0065 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.4922 0.0203 -0.4424 -0.0220 -0.0151 -0.0963 0.0203 0.0000 main_wing + 2 63.969 0.4922 0.0203 -0.4424 0.0220 0.0151 0.0963 0.0203 0.0000 main_wing (YDUP) + 3 20.745 0.0639 0.0065 -0.3136 -0.0100 0.0053 -0.0066 0.0065 0.0000 horizontal_stabilizer + 4 20.745 0.0639 0.0065 -0.3136 0.0100 -0.0053 0.0066 0.0065 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0175 -0.0002 0.0956 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0175 -0.0002 0.0957 -0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.9600 0.0409 0.0000 0.0000 main_wing - 2 63.969 3.715 0.9600 0.0409 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.3902 0.0390 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.3902 0.0390 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.9613 0.0396 0.0000 0.0000 main_wing + 2 63.969 3.715 0.9613 0.0396 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.3894 0.0389 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.3894 0.0389 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0177 -0.0002 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 33.113 0.0176 -0.0002 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_02_01.txt b/regression/scripts/AVL/avl_files/surface_forces_case_02_01.txt index 8ddb84f4ea..e3145901ff 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_02_01.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_02_01.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0087 0.0004 0.0039 0.0001 -0.0002 0.0026 0.0004 0.0000 main_wing - 2 63.969 0.0087 0.0004 0.0039 -0.0001 0.0002 -0.0026 0.0004 0.0000 main_wing (YDUP) - 3 20.745 -0.0279 0.0001 0.1339 0.0045 -0.0028 0.0027 0.0001 0.0000 horizontal_stabilizer - 4 20.745 -0.0279 0.0001 0.1339 -0.0045 0.0028 -0.0027 0.0001 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.0093 0.0004 0.0036 0.0001 -0.0002 0.0026 0.0004 0.0000 main_wing + 2 63.969 0.0093 0.0004 0.0036 -0.0001 0.0002 -0.0026 0.0004 0.0000 main_wing (YDUP) + 3 20.745 -0.0281 0.0001 0.1345 0.0045 -0.0028 0.0027 0.0001 0.0000 horizontal_stabilizer + 4 20.745 -0.0281 0.0001 0.1345 -0.0045 0.0028 -0.0027 0.0001 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0097 0.0002 -0.0240 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal + 6 123.841 -0.0098 0.0002 -0.0239 0.0000 -0.0000 0.0000 0.0002 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.0168 0.0007 0.0000 0.0000 main_wing - 2 63.969 3.715 0.0168 0.0007 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.1702 0.0007 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.1702 0.0007 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.0180 0.0007 0.0000 0.0000 main_wing + 2 63.969 3.715 0.0180 0.0007 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.1711 0.0006 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.1711 0.0006 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0098 0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 -0.0099 0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_02_02.txt b/regression/scripts/AVL/avl_files/surface_forces_case_02_02.txt index 70eadd8ec3..f75e14c4d2 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_02_02.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_02_02.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0906 0.0012 -0.0722 -0.0062 0.0007 -0.0144 0.0012 0.0000 main_wing - 2 63.969 0.0906 0.0012 -0.0722 0.0062 -0.0007 0.0144 0.0012 0.0000 main_wing (YDUP) - 3 20.745 -0.0125 -0.0002 0.0596 0.0020 -0.0012 0.0011 -0.0002 0.0000 horizontal_stabilizer - 4 20.745 -0.0125 -0.0002 0.0596 -0.0020 0.0012 -0.0011 -0.0002 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer + 1 63.969 0.0912 0.0012 -0.0726 -0.0062 0.0007 -0.0145 0.0012 0.0000 main_wing + 2 63.969 0.0912 0.0012 -0.0726 0.0062 -0.0007 0.0145 0.0012 0.0000 main_wing (YDUP) + 3 20.745 -0.0126 -0.0002 0.0602 0.0020 -0.0012 0.0011 -0.0002 0.0000 horizontal_stabilizer + 4 20.745 -0.0126 -0.0002 0.0602 -0.0020 0.0012 -0.0011 -0.0002 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer 6 123.841 -0.0051 0.0000 -0.0036 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.1773 0.0024 0.0000 0.0000 main_wing - 2 63.969 3.715 0.1773 0.0024 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.0760 -0.0011 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.0760 -0.0011 0.0000 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0051 0.0000 0.0000 0.0000 fuselage_horizontal + 1 63.969 3.715 0.1785 0.0023 0.0000 0.0000 main_wing + 2 63.969 3.715 0.1785 0.0023 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.0769 -0.0011 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.0769 -0.0011 0.0000 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer + 6 123.841 33.113 -0.0052 0.0000 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_02_03.txt b/regression/scripts/AVL/avl_files/surface_forces_case_02_03.txt index 95d6502890..d35677cec7 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_02_03.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_02_03.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.1725 0.0031 -0.1484 -0.0115 0.0002 -0.0314 0.0031 0.0000 main_wing - 2 63.969 0.1725 0.0031 -0.1484 0.0115 -0.0002 0.0314 0.0031 0.0000 main_wing (YDUP) - 3 20.745 0.0030 0.0001 -0.0154 -0.0005 0.0003 -0.0005 0.0001 0.0000 horizontal_stabilizer - 4 20.745 0.0030 0.0001 -0.0154 0.0005 -0.0003 0.0005 0.0001 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.1731 0.0031 -0.1487 -0.0114 0.0002 -0.0314 0.0031 0.0000 main_wing + 2 63.969 0.1731 0.0031 -0.1487 0.0114 -0.0002 0.0314 0.0031 0.0000 main_wing (YDUP) + 3 20.745 0.0029 0.0001 -0.0148 -0.0005 0.0003 -0.0004 0.0001 0.0000 horizontal_stabilizer + 4 20.745 0.0029 0.0001 -0.0148 0.0005 -0.0003 0.0004 0.0001 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0005 -0.0001 0.0167 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal + 6 123.841 -0.0005 -0.0001 0.0168 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal 7 123.841 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.3375 0.0061 0.0000 0.0000 main_wing - 2 63.969 3.715 0.3375 0.0061 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.0185 0.0005 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.0185 0.0005 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.3386 0.0060 0.0000 0.0000 main_wing + 2 63.969 3.715 0.3386 0.0060 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.0177 0.0005 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.0177 0.0005 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 -0.0005 -0.0001 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_02_04.txt b/regression/scripts/AVL/avl_files/surface_forces_case_02_04.txt index afd14f384b..54ebd08607 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_02_04.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_02_04.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.2947 0.0080 -0.2618 -0.0176 -0.0031 -0.0565 0.0080 0.0000 main_wing - 2 63.969 0.2947 0.0080 -0.2618 0.0176 0.0031 0.0565 0.0080 0.0000 main_wing (YDUP) - 3 20.745 0.0263 0.0015 -0.1285 -0.0042 0.0024 -0.0028 0.0015 0.0000 horizontal_stabilizer - 4 20.745 0.0263 0.0015 -0.1285 0.0042 -0.0024 0.0028 0.0015 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.2952 0.0078 -0.2621 -0.0175 -0.0031 -0.0566 0.0078 0.0000 main_wing + 2 63.969 0.2952 0.0078 -0.2621 0.0175 0.0031 0.0566 0.0078 0.0000 main_wing (YDUP) + 3 20.745 0.0261 0.0015 -0.1279 -0.0041 0.0024 -0.0028 0.0015 0.0000 horizontal_stabilizer + 4 20.745 0.0261 0.0015 -0.1279 0.0041 -0.0024 0.0028 0.0015 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0064 -0.0002 0.0469 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0063 -0.0002 0.0470 0.0000 -0.0000 -0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.5762 0.0156 0.0000 0.0000 main_wing - 2 63.969 3.715 0.5762 0.0156 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.1601 0.0090 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.1601 0.0090 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.5773 0.0153 0.0000 0.0000 main_wing + 2 63.969 3.715 0.5773 0.0153 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.1593 0.0090 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.1593 0.0090 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 0.0064 -0.0002 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical + 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_02_05.txt b/regression/scripts/AVL/avl_files/surface_forces_case_02_05.txt index 0aabf16260..c132217762 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_02_05.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_02_05.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.3754 0.0125 -0.3363 -0.0204 -0.0069 -0.0729 0.0125 0.0000 main_wing - 2 63.969 0.3754 0.0125 -0.3363 0.0204 0.0069 0.0729 0.0125 0.0000 main_wing (YDUP) - 3 20.745 0.0416 0.0031 -0.2037 -0.0066 0.0036 -0.0044 0.0031 0.0000 horizontal_stabilizer - 4 20.745 0.0416 0.0031 -0.2037 0.0066 -0.0036 0.0044 0.0031 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.3759 0.0122 -0.3366 -0.0202 -0.0069 -0.0730 0.0122 0.0000 main_wing + 2 63.969 0.3759 0.0122 -0.3366 0.0202 0.0069 0.0730 0.0122 0.0000 main_wing (YDUP) + 3 20.745 0.0415 0.0031 -0.2030 -0.0066 0.0036 -0.0043 0.0031 0.0000 horizontal_stabilizer + 4 20.745 0.0415 0.0031 -0.2030 0.0066 -0.0036 0.0043 0.0031 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0109 -0.0002 0.0666 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0108 -0.0002 0.0667 0.0000 0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.7338 0.0244 0.0000 0.0000 main_wing - 2 63.969 3.715 0.7338 0.0244 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.2536 0.0188 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.2536 0.0188 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.7348 0.0239 0.0000 0.0000 main_wing + 2 63.969 3.715 0.7348 0.0239 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.2528 0.0187 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.2528 0.0187 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0110 -0.0002 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 33.113 0.0109 -0.0003 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_02_06.txt b/regression/scripts/AVL/avl_files/surface_forces_case_02_06.txt index 21758ea0c0..9856c0d5af 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_02_06.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_02_06.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.4949 0.0212 -0.4455 -0.0226 -0.0151 -0.0969 0.0212 0.0000 main_wing - 2 63.969 0.4949 0.0212 -0.4455 0.0226 0.0151 0.0969 0.0212 0.0000 main_wing (YDUP) - 3 20.745 0.0642 0.0065 -0.3152 -0.0101 0.0053 -0.0066 0.0065 0.0000 horizontal_stabilizer - 4 20.745 0.0642 0.0065 -0.3152 0.0101 -0.0053 0.0066 0.0065 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.4953 0.0207 -0.4457 -0.0223 -0.0152 -0.0970 0.0207 0.0000 main_wing + 2 63.969 0.4953 0.0207 -0.4457 0.0223 0.0152 0.0970 0.0207 0.0000 main_wing (YDUP) + 3 20.745 0.0641 0.0065 -0.3146 -0.0101 0.0053 -0.0066 0.0065 0.0000 horizontal_stabilizer + 4 20.745 0.0641 0.0065 -0.3146 0.0101 -0.0053 0.0066 0.0065 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0175 -0.0002 0.0955 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0174 -0.0002 0.0956 -0.0000 0.0000 -0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.9667 0.0413 0.0000 0.0000 main_wing - 2 63.969 3.715 0.9667 0.0413 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.3914 0.0393 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.3914 0.0393 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.9676 0.0403 0.0000 0.0000 main_wing + 2 63.969 3.715 0.9676 0.0403 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.3906 0.0392 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.3906 0.0392 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 0.0176 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_03_01.txt b/regression/scripts/AVL/avl_files/surface_forces_case_03_01.txt index 0c504d00a7..6efac01a2b 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_03_01.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_03_01.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0088 0.0004 0.0038 0.0001 -0.0002 0.0026 0.0004 0.0000 main_wing - 2 63.969 0.0088 0.0004 0.0038 -0.0001 0.0002 -0.0026 0.0004 0.0000 main_wing (YDUP) - 3 20.745 -0.0283 0.0001 0.1357 0.0046 -0.0028 0.0028 0.0001 0.0000 horizontal_stabilizer - 4 20.745 -0.0283 0.0001 0.1357 -0.0046 0.0028 -0.0028 0.0001 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0097 0.0002 -0.0241 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal + 1 63.969 0.0094 0.0004 0.0035 0.0001 -0.0002 0.0026 0.0004 0.0000 main_wing + 2 63.969 0.0094 0.0004 0.0035 -0.0001 0.0002 -0.0026 0.0004 0.0000 main_wing (YDUP) + 3 20.745 -0.0284 0.0001 0.1364 0.0046 -0.0028 0.0028 0.0001 0.0000 horizontal_stabilizer + 4 20.745 -0.0284 0.0001 0.1364 -0.0046 0.0028 -0.0028 0.0001 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 vertical_stabilizer + 6 123.841 -0.0098 0.0002 -0.0240 -0.0000 -0.0000 0.0000 0.0002 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.0171 0.0007 0.0000 0.0000 main_wing - 2 63.969 3.715 0.0171 0.0007 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.1725 0.0007 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.1725 0.0007 0.0000 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 4.191 0.0000 0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0098 0.0002 0.0000 0.0000 fuselage_horizontal + 1 63.969 3.715 0.0183 0.0008 0.0000 0.0000 main_wing + 2 63.969 3.715 0.0183 0.0008 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.1734 0.0007 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.1734 0.0007 0.0000 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer + 6 123.841 33.113 -0.0099 0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_03_02.txt b/regression/scripts/AVL/avl_files/surface_forces_case_03_02.txt index 17f2132fd8..66325abcad 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_03_02.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_03_02.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0919 0.0013 -0.0735 -0.0063 0.0007 -0.0147 0.0013 0.0000 main_wing - 2 63.969 0.0919 0.0013 -0.0735 0.0063 -0.0007 0.0147 0.0013 0.0000 main_wing (YDUP) - 3 20.745 -0.0127 -0.0002 0.0608 0.0020 -0.0012 0.0012 -0.0002 0.0000 horizontal_stabilizer - 4 20.745 -0.0127 -0.0002 0.0608 -0.0020 0.0012 -0.0012 -0.0002 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0051 0.0000 -0.0037 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 1 63.969 0.0926 0.0012 -0.0739 -0.0063 0.0007 -0.0147 0.0012 0.0000 main_wing + 2 63.969 0.0926 0.0012 -0.0739 0.0063 -0.0007 0.0147 0.0012 0.0000 main_wing (YDUP) + 3 20.745 -0.0129 -0.0002 0.0614 0.0021 -0.0012 0.0012 -0.0002 0.0000 horizontal_stabilizer + 4 20.745 -0.0129 -0.0002 0.0614 -0.0021 0.0012 -0.0012 -0.0002 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer + 6 123.841 -0.0051 0.0000 -0.0037 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal + 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.1799 0.0024 0.0000 0.0000 main_wing - 2 63.969 3.715 0.1799 0.0024 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.0775 -0.0011 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.0775 -0.0011 0.0000 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0051 0.0000 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 1 63.969 3.715 0.1811 0.0024 0.0000 0.0000 main_wing + 2 63.969 3.715 0.1811 0.0024 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.0784 -0.0011 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.0784 -0.0011 0.0000 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer + 6 123.841 33.113 -0.0052 0.0000 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_03_03.txt b/regression/scripts/AVL/avl_files/surface_forces_case_03_03.txt index 327cd92810..72a24f653e 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_03_03.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_03_03.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.1750 0.0032 -0.1509 -0.0117 0.0002 -0.0319 0.0032 0.0000 main_wing - 2 63.969 0.1750 0.0032 -0.1509 0.0117 -0.0002 0.0319 0.0032 0.0000 main_wing (YDUP) - 3 20.745 0.0029 0.0001 -0.0149 -0.0005 0.0003 -0.0004 0.0001 0.0000 horizontal_stabilizer - 4 20.745 0.0029 0.0001 -0.0149 0.0005 -0.0003 0.0004 0.0001 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.1756 0.0031 -0.1512 -0.0116 0.0002 -0.0319 0.0031 0.0000 main_wing + 2 63.969 0.1756 0.0031 -0.1512 0.0116 -0.0002 0.0319 0.0031 0.0000 main_wing (YDUP) + 3 20.745 0.0028 0.0001 -0.0142 -0.0004 0.0003 -0.0004 0.0001 0.0000 horizontal_stabilizer + 4 20.745 0.0028 0.0001 -0.0142 0.0004 -0.0003 0.0004 0.0001 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer 6 123.841 -0.0005 -0.0001 0.0166 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 7 123.841 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.3423 0.0063 0.0000 0.0000 main_wing - 2 63.969 3.715 0.3423 0.0063 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.0178 0.0005 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.0178 0.0005 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.3435 0.0061 0.0000 0.0000 main_wing + 2 63.969 3.715 0.3435 0.0061 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.0170 0.0005 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.0170 0.0005 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 -0.0005 -0.0001 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_03_04.txt b/regression/scripts/AVL/avl_files/surface_forces_case_03_04.txt index f64490f08f..774a3352e4 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_03_04.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_03_04.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.2989 0.0082 -0.2660 -0.0179 -0.0031 -0.0574 0.0082 0.0000 main_wing - 2 63.969 0.2989 0.0082 -0.2660 0.0179 0.0031 0.0574 0.0082 0.0000 main_wing (YDUP) - 3 20.745 0.0263 0.0015 -0.1289 -0.0042 0.0024 -0.0028 0.0015 0.0000 horizontal_stabilizer - 4 20.745 0.0263 0.0015 -0.1289 0.0042 -0.0024 0.0028 0.0015 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.2995 0.0080 -0.2664 -0.0178 -0.0031 -0.0575 0.0080 0.0000 main_wing + 2 63.969 0.2995 0.0080 -0.2664 0.0178 0.0031 0.0575 0.0080 0.0000 main_wing (YDUP) + 3 20.745 0.0262 0.0015 -0.1282 -0.0042 0.0024 -0.0028 0.0015 0.0000 horizontal_stabilizer + 4 20.745 0.0262 0.0015 -0.1282 0.0042 -0.0024 0.0028 0.0015 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0064 -0.0002 0.0467 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0063 -0.0002 0.0468 -0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.5844 0.0161 0.0000 0.0000 main_wing - 2 63.969 3.715 0.5844 0.0161 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.1606 0.0091 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.1606 0.0091 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.5857 0.0156 0.0000 0.0000 main_wing + 2 63.969 3.715 0.5857 0.0156 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.1597 0.0091 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.1597 0.0091 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0064 -0.0002 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 33.113 0.0063 -0.0002 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_03_05.txt b/regression/scripts/AVL/avl_files/surface_forces_case_03_05.txt index 899aa2bc59..d287b02c9d 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_03_05.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_03_05.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.3807 0.0129 -0.3417 -0.0208 -0.0070 -0.0741 0.0129 0.0000 main_wing - 2 63.969 0.3807 0.0129 -0.3417 0.0208 0.0070 0.0741 0.0129 0.0000 main_wing (YDUP) - 3 20.745 0.0418 0.0032 -0.2047 -0.0066 0.0037 -0.0044 0.0032 0.0000 horizontal_stabilizer - 4 20.745 0.0418 0.0032 -0.2047 0.0066 -0.0037 0.0044 0.0032 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.3814 0.0125 -0.3420 -0.0205 -0.0071 -0.0741 0.0125 0.0000 main_wing + 2 63.969 0.3814 0.0125 -0.3420 0.0205 0.0071 0.0741 0.0125 0.0000 main_wing (YDUP) + 3 20.745 0.0417 0.0032 -0.2040 -0.0066 0.0036 -0.0044 0.0032 0.0000 horizontal_stabilizer + 4 20.745 0.0417 0.0032 -0.2040 0.0066 -0.0036 0.0044 0.0032 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0108 -0.0002 0.0664 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0108 -0.0002 0.0665 -0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.7442 0.0252 0.0000 0.0000 main_wing - 2 63.969 3.715 0.7442 0.0252 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.2549 0.0190 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.2549 0.0190 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.7455 0.0244 0.0000 0.0000 main_wing + 2 63.969 3.715 0.7455 0.0244 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.2540 0.0190 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.2540 0.0190 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 0.0109 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_03_06.txt b/regression/scripts/AVL/avl_files/surface_forces_case_03_06.txt index af0c8afdbf..b761f54345 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_03_06.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_03_06.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.5019 0.0218 -0.4527 -0.0231 -0.0154 -0.0984 0.0218 0.0000 main_wing - 2 63.969 0.5019 0.0218 -0.4526 0.0231 0.0154 0.0984 0.0218 0.0000 main_wing (YDUP) - 3 20.745 0.0646 0.0066 -0.3172 -0.0102 0.0054 -0.0066 0.0066 0.0000 horizontal_stabilizer - 4 20.745 0.0646 0.0066 -0.3172 0.0102 -0.0054 0.0066 0.0066 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.5026 0.0211 -0.4529 -0.0227 -0.0154 -0.0985 0.0211 0.0000 main_wing + 2 63.969 0.5026 0.0211 -0.4529 0.0227 0.0154 0.0985 0.0211 0.0000 main_wing (YDUP) + 3 20.745 0.0645 0.0066 -0.3165 -0.0102 0.0054 -0.0066 0.0066 0.0000 horizontal_stabilizer + 4 20.745 0.0645 0.0066 -0.3165 0.0102 -0.0054 0.0066 0.0066 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0174 -0.0002 0.0953 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 6 123.841 0.0174 -0.0002 0.0953 -0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.9804 0.0426 0.0000 0.0000 main_wing - 2 63.969 3.715 0.9804 0.0426 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.3938 0.0398 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.3938 0.0398 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.9818 0.0413 0.0000 0.0000 main_wing + 2 63.969 3.715 0.9818 0.0413 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.3930 0.0397 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.3930 0.0397 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0176 -0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0175 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_04_01.txt b/regression/scripts/AVL/avl_files/surface_forces_case_04_01.txt index 79fbba260e..65161f9665 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_04_01.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_04_01.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0094 0.0004 0.0034 0.0001 -0.0002 0.0026 0.0004 0.0000 main_wing - 2 63.969 0.0094 0.0004 0.0034 -0.0001 0.0002 -0.0026 0.0004 0.0000 main_wing (YDUP) - 3 20.745 -0.0297 0.0001 0.1427 0.0048 -0.0029 0.0029 0.0001 0.0000 horizontal_stabilizer - 4 20.745 -0.0297 0.0001 0.1427 -0.0048 0.0029 -0.0029 0.0001 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0097 0.0002 -0.0245 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 1 63.969 0.0100 0.0004 0.0030 0.0001 -0.0002 0.0025 0.0004 0.0000 main_wing + 2 63.969 0.0100 0.0004 0.0030 -0.0001 0.0002 -0.0025 0.0004 0.0000 main_wing (YDUP) + 3 20.745 -0.0299 0.0001 0.1434 0.0048 -0.0030 0.0029 0.0001 0.0000 horizontal_stabilizer + 4 20.745 -0.0299 0.0001 0.1434 -0.0048 0.0030 -0.0029 0.0001 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 vertical_stabilizer + 6 123.841 -0.0098 0.0002 -0.0244 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.0183 0.0008 0.0000 0.0000 main_wing - 2 63.969 3.715 0.0183 0.0008 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.1813 0.0008 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.1813 0.0008 0.0000 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 4.191 0.0000 0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0098 0.0002 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 1 63.969 3.715 0.0195 0.0008 0.0000 0.0000 main_wing + 2 63.969 3.715 0.0195 0.0008 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.1823 0.0008 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.1823 0.0008 0.0000 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer + 6 123.841 33.113 -0.0099 0.0002 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_04_02.txt b/regression/scripts/AVL/avl_files/surface_forces_case_04_02.txt index 01dc64c038..6a7f04e7b8 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_04_02.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_04_02.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0971 0.0013 -0.0786 -0.0067 0.0007 -0.0157 0.0013 0.0000 main_wing - 2 63.969 0.0971 0.0013 -0.0786 0.0067 -0.0007 0.0157 0.0013 0.0000 main_wing (YDUP) - 3 20.745 -0.0137 -0.0002 0.0654 0.0022 -0.0013 0.0013 -0.0002 0.0000 horizontal_stabilizer - 4 20.745 -0.0137 -0.0002 0.0654 -0.0022 0.0013 -0.0013 -0.0002 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.0977 0.0013 -0.0790 -0.0067 0.0007 -0.0157 0.0013 0.0000 main_wing + 2 63.969 0.0977 0.0013 -0.0790 0.0067 -0.0007 0.0157 0.0013 0.0000 main_wing (YDUP) + 3 20.745 -0.0138 -0.0002 0.0661 0.0022 -0.0013 0.0013 -0.0002 0.0000 horizontal_stabilizer + 4 20.745 -0.0138 -0.0002 0.0661 -0.0022 0.0013 -0.0013 -0.0002 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0051 0.0000 -0.0042 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 6 123.841 -0.0052 0.0000 -0.0041 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.1899 0.0026 0.0000 0.0000 main_wing - 2 63.969 3.715 0.1899 0.0026 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.0834 -0.0012 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.0834 -0.0012 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.1911 0.0026 0.0000 0.0000 main_wing + 2 63.969 3.715 0.1911 0.0026 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.0844 -0.0012 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.0844 -0.0012 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0051 0.0000 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 33.113 -0.0052 0.0000 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_04_03.txt b/regression/scripts/AVL/avl_files/surface_forces_case_04_03.txt index 68190fa817..f1f55b1e06 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_04_03.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_04_03.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.1846 0.0035 -0.1607 -0.0124 0.0002 -0.0339 0.0035 0.0000 main_wing - 2 63.969 0.1846 0.0035 -0.1607 0.0124 -0.0002 0.0339 0.0035 0.0000 main_wing (YDUP) - 3 20.745 0.0024 0.0001 -0.0126 -0.0004 0.0002 -0.0004 0.0001 0.0000 horizontal_stabilizer - 4 20.745 0.0024 0.0001 -0.0126 0.0004 -0.0002 0.0004 0.0001 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.1853 0.0034 -0.1610 -0.0124 0.0002 -0.0340 0.0034 0.0000 main_wing + 2 63.969 0.1853 0.0034 -0.1610 0.0124 -0.0002 0.0340 0.0034 0.0000 main_wing (YDUP) + 3 20.745 0.0023 0.0001 -0.0119 -0.0004 0.0002 -0.0004 0.0001 0.0000 horizontal_stabilizer + 4 20.745 0.0023 0.0001 -0.0119 0.0004 -0.0002 0.0004 0.0001 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0005 -0.0001 0.0160 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal + 6 123.841 -0.0006 -0.0001 0.0161 -0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.3612 0.0069 0.0000 0.0000 main_wing - 2 63.969 3.715 0.3612 0.0069 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.0149 0.0004 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.0149 0.0004 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.3624 0.0066 0.0000 0.0000 main_wing + 2 63.969 3.715 0.3624 0.0066 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.0140 0.0004 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.0140 0.0004 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0005 -0.0001 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 -0.0006 -0.0001 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_04_04.txt b/regression/scripts/AVL/avl_files/surface_forces_case_04_04.txt index 8b20fa8d24..8a0d7df992 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_04_04.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_04_04.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.3153 0.0091 -0.2828 -0.0191 -0.0033 -0.0609 0.0091 0.0000 main_wing - 2 63.969 0.3153 0.0091 -0.2828 0.0191 0.0033 0.0609 0.0091 0.0000 main_wing (YDUP) - 3 20.745 0.0266 0.0016 -0.1301 -0.0042 0.0024 -0.0029 0.0016 0.0000 horizontal_stabilizer - 4 20.745 0.0266 0.0016 -0.1301 0.0042 -0.0024 0.0028 0.0016 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.3159 0.0087 -0.2831 -0.0189 -0.0033 -0.0610 0.0087 0.0000 main_wing + 2 63.969 0.3159 0.0087 -0.2831 0.0189 0.0033 0.0610 0.0087 0.0000 main_wing (YDUP) + 3 20.745 0.0265 0.0016 -0.1294 -0.0042 0.0024 -0.0028 0.0016 0.0000 horizontal_stabilizer + 4 20.745 0.0265 0.0016 -0.1294 0.0042 -0.0024 0.0028 0.0016 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0063 -0.0002 0.0460 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0062 -0.0002 0.0461 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.6166 0.0177 0.0000 0.0000 main_wing - 2 63.969 3.715 0.6166 0.0177 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.1621 0.0094 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.1621 0.0094 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.6176 0.0170 0.0000 0.0000 main_wing + 2 63.969 3.715 0.6176 0.0170 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.1612 0.0094 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.1612 0.0094 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0063 -0.0002 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 33.113 0.0062 -0.0002 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_04_05.txt b/regression/scripts/AVL/avl_files/surface_forces_case_04_05.txt index fcb0b1a106..3659f22fa1 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_04_05.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_04_05.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.4016 0.0143 -0.3631 -0.0223 -0.0075 -0.0786 0.0143 0.0000 main_wing - 2 63.969 0.4016 0.0143 -0.3631 0.0223 0.0075 0.0786 0.0143 0.0000 main_wing (YDUP) - 3 20.745 0.0426 0.0033 -0.2083 -0.0068 0.0038 -0.0045 0.0033 0.0000 horizontal_stabilizer - 4 20.745 0.0426 0.0033 -0.2083 0.0068 -0.0038 0.0045 0.0033 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.4021 0.0137 -0.3634 -0.0220 -0.0075 -0.0786 0.0137 0.0000 main_wing + 2 63.969 0.4021 0.0137 -0.3634 0.0220 0.0075 0.0786 0.0137 0.0000 main_wing (YDUP) + 3 20.745 0.0424 0.0033 -0.2076 -0.0068 0.0037 -0.0044 0.0033 0.0000 horizontal_stabilizer + 4 20.745 0.0424 0.0033 -0.2076 0.0068 -0.0037 0.0044 0.0033 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0107 -0.0002 0.0657 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0106 -0.0002 0.0657 0.0000 0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.7851 0.0278 0.0000 0.0000 main_wing - 2 63.969 3.715 0.7851 0.0278 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.2594 0.0199 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.2594 0.0199 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.7860 0.0268 0.0000 0.0000 main_wing + 2 63.969 3.715 0.7860 0.0268 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.2585 0.0198 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.2585 0.0198 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0108 -0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0107 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_04_06.txt b/regression/scripts/AVL/avl_files/surface_forces_case_04_06.txt index 4c5426e7bd..305447ed1e 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_04_06.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_04_06.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.5293 0.0241 -0.4809 -0.0250 -0.0163 -0.1044 0.0241 0.0000 main_wing - 2 63.969 0.5293 0.0241 -0.4809 0.0250 0.0163 0.1044 0.0241 0.0000 main_wing (YDUP) - 3 20.745 0.0661 0.0069 -0.3243 -0.0105 0.0056 -0.0068 0.0069 0.0000 horizontal_stabilizer - 4 20.745 0.0661 0.0069 -0.3243 0.0105 -0.0056 0.0068 0.0069 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.5298 0.0232 -0.4810 -0.0244 -0.0164 -0.1044 0.0232 0.0000 main_wing + 2 63.969 0.5298 0.0232 -0.4810 0.0244 0.0164 0.1044 0.0232 0.0000 main_wing (YDUP) + 3 20.745 0.0659 0.0069 -0.3236 -0.0105 0.0056 -0.0068 0.0069 0.0000 horizontal_stabilizer + 4 20.745 0.0659 0.0069 -0.3236 0.0105 -0.0056 0.0068 0.0069 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0172 -0.0002 0.0943 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0171 -0.0002 0.0944 -0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 1.0341 0.0471 0.0000 0.0000 main_wing - 2 63.969 3.715 1.0341 0.0471 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.4027 0.0418 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.4027 0.0418 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 1.0349 0.0454 0.0000 0.0000 main_wing + 2 63.969 3.715 1.0349 0.0454 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.4017 0.0417 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.4017 0.0417 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 0.0173 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_05_01.txt b/regression/scripts/AVL/avl_files/surface_forces_case_05_01.txt index 2e29dc14cd..6ef5ecf530 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_05_01.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_05_01.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0106 0.0004 0.0023 0.0000 -0.0002 0.0026 0.0004 0.0000 main_wing - 2 63.969 0.0106 0.0004 0.0023 -0.0000 0.0002 -0.0026 0.0004 0.0000 main_wing (YDUP) - 3 20.745 -0.0326 0.0002 0.1567 0.0052 -0.0032 0.0032 0.0002 0.0000 horizontal_stabilizer - 4 20.745 -0.0326 0.0002 0.1567 -0.0052 0.0032 -0.0032 0.0002 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0097 0.0002 -0.0252 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal + 1 63.969 0.0114 0.0004 0.0019 -0.0000 -0.0002 0.0025 0.0004 0.0000 main_wing + 2 63.969 0.0114 0.0004 0.0019 0.0000 0.0002 -0.0025 0.0004 0.0000 main_wing (YDUP) + 3 20.745 -0.0328 0.0002 0.1575 0.0053 -0.0032 0.0032 0.0002 0.0000 horizontal_stabilizer + 4 20.745 -0.0328 0.0002 0.1575 -0.0053 0.0032 -0.0032 0.0002 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 -0.0000 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer + 6 123.841 -0.0097 0.0002 -0.0251 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.0207 0.0008 0.0000 0.0000 main_wing - 2 63.969 3.715 0.0207 0.0008 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.1989 0.0011 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.1989 0.0011 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.0222 0.0009 0.0000 0.0000 main_wing + 2 63.969 3.715 0.0222 0.0009 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.2000 0.0010 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.2000 0.0010 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 0.0000 0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 -0.0098 0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_05_02.txt b/regression/scripts/AVL/avl_files/surface_forces_case_05_02.txt index 8478e4949d..9a7116f07b 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_05_02.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_05_02.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.1075 0.0015 -0.0894 -0.0075 0.0008 -0.0178 0.0015 0.0000 main_wing - 2 63.969 0.1075 0.0015 -0.0894 0.0075 -0.0008 0.0178 0.0015 0.0000 main_wing (YDUP) - 3 20.745 -0.0157 -0.0002 0.0751 0.0025 -0.0015 0.0015 -0.0002 0.0000 horizontal_stabilizer - 4 20.745 -0.0157 -0.0002 0.0751 -0.0025 0.0015 -0.0015 -0.0002 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 0.0000 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0051 0.0000 -0.0051 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_horizontal + 1 63.969 0.1083 0.0015 -0.0898 -0.0075 0.0008 -0.0179 0.0015 0.0000 main_wing + 2 63.969 0.1083 0.0015 -0.0898 0.0075 -0.0008 0.0179 0.0015 0.0000 main_wing (YDUP) + 3 20.745 -0.0159 -0.0002 0.0759 0.0026 -0.0015 0.0015 -0.0002 0.0000 horizontal_stabilizer + 4 20.745 -0.0159 -0.0002 0.0759 -0.0026 0.0015 -0.0015 -0.0002 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 0.0000 -0.0000 -0.0000 -0.0000 0.0000 -0.0000 -0.0000 0.0000 vertical_stabilizer + 6 123.841 -0.0052 0.0000 -0.0050 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.2104 0.0030 0.0000 0.0000 main_wing - 2 63.969 3.715 0.2104 0.0030 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.0956 -0.0014 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.0956 -0.0014 0.0000 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 4.191 0.0000 0.0000 0.0000 0.0000 vertical_stabilizer + 1 63.969 3.715 0.2119 0.0030 0.0000 0.0000 main_wing + 2 63.969 3.715 0.2119 0.0030 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.0967 -0.0014 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.0967 -0.0014 0.0000 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 4.191 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 -0.0052 0.0000 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_05_03.txt b/regression/scripts/AVL/avl_files/surface_forces_case_05_03.txt index a0c92d02b0..35496a2250 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_05_03.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_05_03.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.2043 0.0041 -0.1811 -0.0140 0.0002 -0.0381 0.0041 0.0000 main_wing - 2 63.969 0.2043 0.0041 -0.1811 0.0140 -0.0002 0.0381 0.0041 0.0000 main_wing (YDUP) - 3 20.745 0.0014 0.0000 -0.0073 -0.0002 0.0001 -0.0003 0.0000 0.0000 horizontal_stabilizer - 4 20.745 0.0014 0.0000 -0.0073 0.0002 -0.0001 0.0003 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.2051 0.0041 -0.1815 -0.0140 0.0002 -0.0382 0.0041 0.0000 main_wing + 2 63.969 0.2051 0.0041 -0.1815 0.0140 -0.0002 0.0382 0.0041 0.0000 main_wing (YDUP) + 3 20.745 0.0012 0.0000 -0.0065 -0.0002 0.0001 -0.0003 0.0000 0.0000 horizontal_stabilizer + 4 20.745 0.0012 0.0000 -0.0065 0.0002 -0.0001 0.0003 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0006 -0.0001 0.0149 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 6 123.841 -0.0007 -0.0001 0.0150 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal + 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.3998 0.0081 0.0000 0.0000 main_wing - 2 63.969 3.715 0.3998 0.0081 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.0082 0.0002 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.0082 0.0002 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.4014 0.0080 0.0000 0.0000 main_wing + 2 63.969 3.715 0.4014 0.0080 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.0071 0.0002 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.0071 0.0002 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0006 -0.0001 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 33.113 -0.0007 -0.0001 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_05_04.txt b/regression/scripts/AVL/avl_files/surface_forces_case_05_04.txt index 4c788dc7fc..6739f5a0bb 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_05_04.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_05_04.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.3488 0.0108 -0.3177 -0.0216 -0.0038 -0.0682 0.0108 0.0000 main_wing - 2 63.969 0.3488 0.0108 -0.3177 0.0216 0.0038 0.0682 0.0108 0.0000 main_wing (YDUP) - 3 20.745 0.0269 0.0017 -0.1314 -0.0043 0.0025 -0.0029 0.0017 0.0000 horizontal_stabilizer - 4 20.745 0.0269 0.0017 -0.1314 0.0043 -0.0025 0.0029 0.0017 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.3497 0.0107 -0.3182 -0.0216 -0.0038 -0.0682 0.0107 0.0000 main_wing + 2 63.969 0.3497 0.0107 -0.3182 0.0216 0.0038 0.0682 0.0107 0.0000 main_wing (YDUP) + 3 20.745 0.0267 0.0017 -0.1306 -0.0043 0.0025 -0.0029 0.0017 0.0000 horizontal_stabilizer + 4 20.745 0.0267 0.0017 -0.1306 0.0043 -0.0025 0.0029 0.0017 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0061 -0.0002 0.0446 0.0000 -0.0000 -0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0060 -0.0002 0.0447 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.6821 0.0210 0.0000 0.0000 main_wing - 2 63.969 3.715 0.6821 0.0210 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.1637 0.0100 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.1637 0.0100 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.6838 0.0208 0.0000 0.0000 main_wing + 2 63.969 3.715 0.6838 0.0208 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.1626 0.0099 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.1626 0.0099 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 0.0061 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_05_05.txt b/regression/scripts/AVL/avl_files/surface_forces_case_05_05.txt index 170bf7d38a..f613874086 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_05_05.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_05_05.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.4442 0.0170 -0.4076 -0.0253 -0.0084 -0.0878 0.0170 0.0000 main_wing - 2 63.969 0.4442 0.0170 -0.4076 0.0253 0.0084 0.0878 0.0170 0.0000 main_wing (YDUP) - 3 20.745 0.0437 0.0036 -0.2140 -0.0071 0.0039 -0.0046 0.0036 0.0000 horizontal_stabilizer - 4 20.745 0.0437 0.0036 -0.2140 0.0071 -0.0039 0.0046 0.0036 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.4452 0.0168 -0.4080 -0.0252 -0.0084 -0.0879 0.0168 0.0000 main_wing + 2 63.969 0.4452 0.0168 -0.4080 0.0252 0.0084 0.0879 0.0168 0.0000 main_wing (YDUP) + 3 20.745 0.0435 0.0035 -0.2131 -0.0071 0.0039 -0.0046 0.0035 0.0000 horizontal_stabilizer + 4 20.745 0.0435 0.0035 -0.2131 0.0071 -0.0039 0.0046 0.0035 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0104 -0.0002 0.0640 0.0000 -0.0000 -0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0104 -0.0002 0.0641 -0.0000 -0.0000 -0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.8684 0.0332 0.0000 0.0000 main_wing - 2 63.969 3.715 0.8684 0.0332 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.2664 0.0214 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.2664 0.0214 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.8703 0.0329 0.0000 0.0000 main_wing + 2 63.969 3.715 0.8703 0.0329 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.2653 0.0214 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.2653 0.0214 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0105 -0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0104 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_05_06.txt b/regression/scripts/AVL/avl_files/surface_forces_case_05_06.txt index 3d3025f27b..7c25c0200e 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_05_06.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_05_06.txt @@ -6,21 +6,21 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.5853 0.0290 -0.5394 -0.0287 -0.0183 -0.1165 0.0290 0.0000 main_wing - 2 63.969 0.5853 0.0290 -0.5394 0.0287 0.0183 0.1165 0.0290 0.0000 main_wing (YDUP) - 3 20.745 0.0685 0.0076 -0.3364 -0.0112 0.0060 -0.0071 0.0076 0.0000 horizontal_stabilizer - 4 20.745 0.0685 0.0076 -0.3364 0.0112 -0.0060 0.0071 0.0076 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.5864 0.0286 -0.5399 -0.0285 -0.0183 -0.1167 0.0286 0.0000 main_wing + 2 63.969 0.5864 0.0286 -0.5399 0.0285 0.0183 0.1167 0.0286 0.0000 main_wing (YDUP) + 3 20.745 0.0683 0.0076 -0.3356 -0.0111 0.0059 -0.0071 0.0076 0.0000 horizontal_stabilizer + 4 20.745 0.0683 0.0076 -0.3356 0.0111 -0.0059 0.0071 0.0076 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0168 -0.0001 0.0923 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal - 7 123.841 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0167 -0.0001 0.0924 -0.0000 0.0000 -0.0000 -0.0001 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 1.1436 0.0565 0.0000 0.0000 main_wing - 2 63.969 3.715 1.1436 0.0565 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.4177 0.0457 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.4177 0.0457 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 1.1458 0.0559 0.0000 0.0000 main_wing + 2 63.969 3.715 1.1458 0.0559 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.4166 0.0455 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.4166 0.0455 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 0.0169 -0.0001 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_06_01.txt b/regression/scripts/AVL/avl_files/surface_forces_case_06_01.txt index 38c0ab2a75..1cb329c233 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_06_01.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_06_01.txt @@ -6,10 +6,10 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.0139 0.0005 -0.0013 -0.0002 -0.0002 0.0022 0.0005 0.0000 main_wing - 2 63.969 0.0139 0.0005 -0.0013 0.0002 0.0002 -0.0022 0.0005 0.0000 main_wing (YDUP) - 3 20.745 -0.0389 0.0003 0.1869 0.0062 -0.0038 0.0038 0.0003 0.0000 horizontal_stabilizer - 4 20.745 -0.0389 0.0003 0.1869 -0.0062 0.0038 -0.0038 0.0003 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.0148 0.0005 -0.0018 -0.0002 -0.0001 0.0022 0.0005 0.0000 main_wing + 2 63.969 0.0148 0.0005 -0.0018 0.0002 0.0001 -0.0022 0.0005 0.0000 main_wing (YDUP) + 3 20.745 -0.0391 0.0003 0.1882 0.0062 -0.0039 0.0039 0.0003 0.0000 horizontal_stabilizer + 4 20.745 -0.0391 0.0003 0.1882 -0.0062 0.0039 -0.0039 0.0003 0.0000 horizontal_stabilizer (YDUP) 5 34.910 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 -0.0096 0.0002 -0.0266 -0.0000 0.0000 0.0000 0.0002 0.0000 fuselage_horizontal 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical @@ -17,11 +17,11 @@ Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.0271 0.0010 0.0000 0.0000 main_wing - 2 63.969 3.715 0.0271 0.0010 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.2368 0.0017 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.2368 0.0017 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.0289 0.0010 0.0000 0.0000 main_wing + 2 63.969 3.715 0.0289 0.0010 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.2385 0.0017 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.2385 0.0017 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 0.0000 0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0096 0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 -0.0097 0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_06_02.txt b/regression/scripts/AVL/avl_files/surface_forces_case_06_02.txt index 5d10fcc0a5..fa8b6a2e6d 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_06_02.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_06_02.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.1316 0.0020 -0.1155 -0.0095 0.0010 -0.0228 0.0020 0.0000 main_wing - 2 63.969 0.1316 0.0020 -0.1155 0.0095 -0.0010 0.0228 0.0020 0.0000 main_wing (YDUP) - 3 20.745 -0.0203 -0.0003 0.0976 0.0033 -0.0020 0.0019 -0.0003 0.0000 horizontal_stabilizer - 4 20.745 -0.0203 -0.0003 0.0976 -0.0033 0.0020 -0.0019 -0.0003 0.0000 horizontal_stabilizer (YDUP) - 5 34.910 0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0051 0.0000 -0.0070 -0.0000 0.0000 0.0000 0.0000 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 1 63.969 0.1326 0.0021 -0.1160 -0.0095 0.0010 -0.0229 0.0021 0.0000 main_wing + 2 63.969 0.1326 0.0021 -0.1160 0.0095 -0.0010 0.0229 0.0021 0.0000 main_wing (YDUP) + 3 20.745 -0.0206 -0.0003 0.0989 0.0033 -0.0020 0.0020 -0.0003 0.0000 horizontal_stabilizer + 4 20.745 -0.0206 -0.0003 0.0989 -0.0033 0.0020 -0.0020 -0.0003 0.0000 horizontal_stabilizer (YDUP) + 5 34.910 0.0000 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer + 6 123.841 -0.0052 0.0000 -0.0069 -0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_horizontal + 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.2576 0.0040 0.0000 0.0000 main_wing - 2 63.969 3.715 0.2576 0.0040 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.1239 -0.0018 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.1239 -0.0018 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.2595 0.0040 0.0000 0.0000 main_wing + 2 63.969 3.715 0.2595 0.0040 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.1255 -0.0018 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.1255 -0.0018 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 0.0000 0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 -0.0051 0.0000 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 33.113 -0.0052 0.0000 0.0000 0.0000 fuselage_horizontal + 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_06_03.txt b/regression/scripts/AVL/avl_files/surface_forces_case_06_03.txt index 23dace451c..e9e077d796 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_06_03.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_06_03.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.2493 0.0058 -0.2298 -0.0176 0.0002 -0.0478 0.0058 0.0000 main_wing - 2 63.969 0.2493 0.0058 -0.2298 0.0176 -0.0002 0.0478 0.0058 0.0000 main_wing (YDUP) - 3 20.745 -0.0017 -0.0001 0.0075 0.0003 -0.0002 0.0000 -0.0001 0.0000 horizontal_stabilizer - 4 20.745 -0.0017 -0.0001 0.0075 -0.0003 0.0002 -0.0000 -0.0001 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.2503 0.0058 -0.2303 -0.0176 0.0002 -0.0479 0.0058 0.0000 main_wing + 2 63.969 0.2503 0.0058 -0.2303 0.0176 -0.0002 0.0479 0.0058 0.0000 main_wing (YDUP) + 3 20.745 -0.0020 -0.0001 0.0087 0.0003 -0.0002 0.0001 -0.0001 0.0000 horizontal_stabilizer + 4 20.745 -0.0020 -0.0001 0.0087 -0.0003 0.0002 -0.0001 -0.0001 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 -0.0007 -0.0001 0.0126 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal - 7 123.841 -0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_vertical + 6 123.841 -0.0007 -0.0001 0.0127 -0.0000 -0.0000 -0.0000 -0.0001 0.0000 fuselage_horizontal + 7 123.841 -0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.4878 0.0112 0.0000 0.0000 main_wing - 2 63.969 3.715 0.4878 0.0112 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 -0.0104 -0.0004 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 -0.0103 -0.0004 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.4898 0.0113 0.0000 0.0000 main_wing + 2 63.969 3.715 0.4898 0.0113 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 -0.0120 -0.0005 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 -0.0120 -0.0005 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer 6 123.841 33.113 -0.0007 -0.0001 0.0000 0.0000 fuselage_horizontal - 7 123.841 33.113 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_06_04.txt b/regression/scripts/AVL/avl_files/surface_forces_case_06_04.txt index 22e0481d7d..3872e9c1cb 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_06_04.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_06_04.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.4249 0.0154 -0.4004 -0.0275 -0.0047 -0.0849 0.0154 0.0000 main_wing - 2 63.969 0.4249 0.0154 -0.4004 0.0275 0.0047 0.0849 0.0154 0.0000 main_wing (YDUP) - 3 20.745 0.0262 0.0018 -0.1284 -0.0043 0.0025 -0.0028 0.0018 0.0000 horizontal_stabilizer - 4 20.745 0.0262 0.0018 -0.1284 0.0043 -0.0025 0.0028 0.0018 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.4259 0.0154 -0.4009 -0.0276 -0.0048 -0.0850 0.0154 0.0000 main_wing + 2 63.969 0.4259 0.0154 -0.4009 0.0276 0.0048 0.0850 0.0154 0.0000 main_wing (YDUP) + 3 20.745 0.0259 0.0018 -0.1271 -0.0043 0.0025 -0.0028 0.0018 0.0000 horizontal_stabilizer + 4 20.745 0.0259 0.0018 -0.1271 0.0043 -0.0025 0.0028 0.0018 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0058 -0.0002 0.0416 0.0000 -0.0000 0.0000 -0.0002 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0057 -0.0002 0.0416 -0.0000 -0.0000 -0.0000 -0.0002 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 0.8311 0.0300 0.0000 0.0000 main_wing - 2 63.969 3.715 0.8311 0.0300 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.1598 0.0107 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.1598 0.0107 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 0.8330 0.0301 0.0000 0.0000 main_wing + 2 63.969 3.715 0.8330 0.0301 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.1583 0.0106 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.1583 0.0106 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0059 -0.0002 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0058 -0.0002 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_06_05.txt b/regression/scripts/AVL/avl_files/surface_forces_case_06_05.txt index 7024f532e4..93c61a1112 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_06_05.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_06_05.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.5408 0.0245 -0.5127 -0.0326 -0.0105 -0.1091 0.0245 0.0000 main_wing - 2 63.969 0.5408 0.0245 -0.5127 0.0326 0.0105 0.1091 0.0245 0.0000 main_wing (YDUP) - 3 20.745 0.0446 0.0040 -0.2187 -0.0075 0.0042 -0.0047 0.0040 0.0000 horizontal_stabilizer - 4 20.745 0.0446 0.0040 -0.2187 0.0075 -0.0042 0.0047 0.0040 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.5418 0.0245 -0.5132 -0.0326 -0.0106 -0.1092 0.0245 0.0000 main_wing + 2 63.969 0.5418 0.0245 -0.5132 0.0326 0.0106 0.1092 0.0245 0.0000 main_wing (YDUP) + 3 20.745 0.0444 0.0040 -0.2174 -0.0074 0.0042 -0.0047 0.0040 0.0000 horizontal_stabilizer + 4 20.745 0.0444 0.0040 -0.2174 0.0074 -0.0042 0.0047 0.0040 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0100 -0.0001 0.0604 0.0000 -0.0000 0.0000 -0.0001 0.0000 fuselage_horizontal - 7 123.841 0.0000 0.0000 0.0000 0.0000 -0.0000 -0.0000 0.0000 0.0000 fuselage_vertical + 6 123.841 0.0100 -0.0001 0.0605 -0.0000 0.0000 -0.0000 -0.0001 0.0000 fuselage_horizontal + 7 123.841 0.0000 0.0000 -0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 1.0574 0.0478 0.0000 0.0000 main_wing - 2 63.969 3.715 1.0574 0.0478 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.2722 0.0240 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.2722 0.0240 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 1.0594 0.0479 0.0000 0.0000 main_wing + 2 63.969 3.715 1.0594 0.0479 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.2707 0.0239 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.2707 0.0239 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0101 -0.0001 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0100 -0.0001 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/avl_files/surface_forces_case_06_06.txt b/regression/scripts/AVL/avl_files/surface_forces_case_06_06.txt index ec8a01d72c..886b26052b 100644 --- a/regression/scripts/AVL/avl_files/surface_forces_case_06_06.txt +++ b/regression/scripts/AVL/avl_files/surface_forces_case_06_06.txt @@ -6,22 +6,22 @@ Xref = 15.3099 Yref = 0.0000 Zref = -0.4802 n Area CL CD Cm CY Cn Cl CDi CDv - 1 63.969 0.7119 0.0419 -0.6778 -0.0379 -0.0229 -0.1445 0.0419 0.0000 main_wing - 2 63.969 0.7119 0.0419 -0.6778 0.0379 0.0229 0.1445 0.0419 0.0000 main_wing (YDUP) - 3 20.745 0.0717 0.0088 -0.3527 -0.0122 0.0066 -0.0074 0.0088 0.0000 horizontal_stabilizer - 4 20.745 0.0717 0.0088 -0.3527 0.0122 -0.0066 0.0074 0.0088 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 0.7130 0.0419 -0.6781 -0.0379 -0.0229 -0.1446 0.0419 0.0000 main_wing + 2 63.969 0.7130 0.0419 -0.6781 0.0379 0.0229 0.1446 0.0419 0.0000 main_wing (YDUP) + 3 20.745 0.0714 0.0087 -0.3514 -0.0122 0.0066 -0.0074 0.0087 0.0000 horizontal_stabilizer + 4 20.745 0.0714 0.0087 -0.3514 0.0122 -0.0066 0.0074 0.0087 0.0000 horizontal_stabilizer (YDUP) 5 34.910 0.0000 -0.0000 -0.0000 0.0000 -0.0000 0.0000 -0.0000 0.0000 vertical_stabilizer - 6 123.841 0.0161 -0.0000 0.0879 -0.0000 -0.0000 0.0000 -0.0000 0.0000 fuselage_horizontal + 6 123.841 0.0161 -0.0001 0.0880 0.0000 0.0000 -0.0000 -0.0001 0.0000 fuselage_horizontal 7 123.841 -0.0000 0.0000 0.0000 0.0000 0.0000 -0.0000 0.0000 0.0000 fuselage_vertical Surface Forces (referred to Ssurf, Cave about root LE on hinge axis) n Ssurf Cave cl cd cdv cm_LE - 1 63.969 3.715 1.3914 0.0817 0.0000 0.0000 main_wing - 2 63.969 3.715 1.3914 0.0817 0.0000 0.0000 main_wing (YDUP) - 3 20.745 2.849 0.4376 0.0527 0.0000 0.0000 horizontal_stabilizer - 4 20.745 2.849 0.4376 0.0527 0.0000 0.0000 horizontal_stabilizer (YDUP) + 1 63.969 3.715 1.3935 0.0818 0.0000 0.0000 main_wing + 2 63.969 3.715 1.3935 0.0818 0.0000 0.0000 main_wing (YDUP) + 3 20.745 2.849 0.4361 0.0525 0.0000 0.0000 horizontal_stabilizer + 4 20.745 2.849 0.4361 0.0525 0.0000 0.0000 horizontal_stabilizer (YDUP) 5 34.910 4.191 -0.0000 -0.0000 0.0000 0.0000 vertical_stabilizer - 6 123.841 33.113 0.0163 -0.0000 0.0000 0.0000 fuselage_horizontal + 6 123.841 33.113 0.0162 -0.0001 0.0000 0.0000 fuselage_horizontal 7 123.841 33.113 -0.0000 0.0000 0.0000 0.0000 fuselage_vertical --------------------------------------------------------------- diff --git a/regression/scripts/AVL/cruise_aero_data.txt b/regression/scripts/AVL/cruise_aero_data.txt index c3e03c018c..073709a833 100644 --- a/regression/scripts/AVL/cruise_aero_data.txt +++ b/regression/scripts/AVL/cruise_aero_data.txt @@ -1,37 +1,37 @@ # CL CD e --0.04701000 0.00116230 0.09220000 --0.04723000 0.00116840 0.09240000 --0.04768000 0.00118780 0.09270000 --0.04937000 0.00125620 0.09360000 --0.05252000 0.00140870 0.09480000 --0.05827000 0.00175690 0.09370000 -0.14705000 0.00205270 0.52290000 -0.14805000 0.00206320 0.52520000 -0.15012000 0.00211570 0.53000000 -0.15823000 0.00227700 0.54830000 -0.17483000 0.00260060 0.58310000 -0.21291000 0.00344640 0.64840000 -0.34102000 0.00613230 0.78650000 -0.34324000 0.00617850 0.78850000 -0.34783000 0.00635120 0.79280000 -0.36574000 0.00691610 0.80860000 -0.40212000 0.00805510 0.83750000 -0.48408000 0.01103990 0.88740000 -0.63055000 0.01819130 0.84140000 -0.63462000 0.01835070 0.84320000 -0.64294000 0.01886560 0.84680000 -0.67548000 0.02061640 0.86030000 -0.74137000 0.02418500 0.88470000 -0.88876000 0.03344790 0.92650000 -0.82179000 0.03009990 0.84850000 -0.82709000 0.03037520 0.85030000 -0.83787000 0.03122350 0.85370000 -0.88003000 0.03414370 0.86660000 -0.96537000 0.04012310 0.88990000 -1.15578000 0.05557930 0.92980000 -1.10462000 0.05349390 0.85160000 -1.11173000 0.05400270 0.85320000 -1.12612000 0.05550170 0.85650000 -1.18241000 0.06071890 0.86900000 -1.29636000 0.07145320 0.89120000 -1.54987000 0.09908440 0.92970000 +-0.04716000 0.00118000 0.08730000 +-0.04738000 0.00120000 0.08750000 +-0.04781000 0.00121000 0.08770000 +-0.04950000 0.00128000 0.08860000 +-0.05261000 0.00144000 0.08950000 +-0.05822000 0.00182000 0.08790000 +0.15111000 0.00202000 0.51810000 +0.15211000 0.00207000 0.52040000 +0.15427000 0.00209000 0.52520000 +0.16256000 0.00224000 0.54330000 +0.17970000 0.00263000 0.57770000 +0.21886000 0.00357000 0.64260000 +0.34929000 0.00606000 0.78340000 +0.35149000 0.00618000 0.78550000 +0.35627000 0.00629000 0.78970000 +0.37451000 0.00681000 0.80560000 +0.41198000 0.00813000 0.83450000 +0.49594000 0.01135000 0.88440000 +0.64511000 0.01807000 0.84010000 +0.64908000 0.01839000 0.84190000 +0.65781000 0.01875000 0.84550000 +0.69083000 0.02038000 0.85910000 +0.75874000 0.02444000 0.88350000 +0.90943000 0.03424000 0.92550000 +0.84054000 0.02995000 0.84770000 +0.84564000 0.03046000 0.84940000 +0.85700000 0.03107000 0.85290000 +0.89972000 0.03381000 0.86580000 +0.98774000 0.04058000 0.88910000 +1.18227000 0.05684000 0.92910000 +1.12960000 0.05332000 0.85100000 +1.13633000 0.05417000 0.85270000 +1.15160000 0.05531000 0.85600000 +1.20853000 0.06019000 0.86850000 +1.32619000 0.07231000 0.89080000 +1.58496000 0.10125000 0.92930000 diff --git a/regression/scripts/AVL/cruise_stability_data.txt b/regression/scripts/AVL/cruise_stability_data.txt index df86b8c296..a4e09e9489 100644 --- a/regression/scripts/AVL/cruise_stability_data.txt +++ b/regression/scripts/AVL/cruise_stability_data.txt @@ -1,37 +1,37 @@ # CM Cm_alpha Cn_beta NP -0.25003000 -7.95372600 0.27195000 0.27195000 -0.25163000 -8.00371500 0.27314500 0.27314500 -0.25494000 -8.10744800 0.27559500 0.27559500 -0.26769000 -8.50939800 0.28485700 0.28485700 -0.29265000 -9.30981600 0.30220300 0.30220300 -0.34458000 -11.04503500 0.33530200 0.33530200 --0.02877000 -8.01405000 0.27647200 0.27647200 --0.02893000 -8.06478200 0.27770800 0.27770800 --0.02926000 -8.16925200 0.28023900 0.28023900 --0.03060000 -8.57448900 0.28982100 0.28982100 --0.03371000 -9.38183900 0.30780800 0.30780800 --0.04266000 -11.13316700 0.34232400 0.34232400 --0.30900000 -8.03533000 0.28199900 0.28199900 --0.31094000 -8.08656300 0.28328500 0.28328500 --0.31492000 -8.19125900 0.28591600 0.28591600 --0.33044000 -8.59780700 0.29589100 0.29589100 --0.36179000 -9.40815100 0.31466900 0.31466900 --0.43203000 -11.16706200 0.35094600 0.35094600 --0.72902000 -7.99386600 0.29211600 0.29211600 --0.73366000 -8.04538300 0.29349100 0.29349100 --0.74311000 -8.14946400 0.29630700 0.29630700 --0.77989000 -8.55426400 0.30700200 0.30700200 --0.85363000 -9.36170000 0.32723900 0.32723900 --1.01593000 -11.11591400 0.36678500 0.36678500 --1.00684000 -7.91750000 0.30002900 0.30002900 --1.01328000 -7.96889200 0.30147500 0.30147500 --1.02634000 -8.07192400 0.30443400 0.30443400 --1.07719000 -8.47309300 0.31569400 0.31569400 --1.17901000 -9.27367200 0.33707700 0.33707700 --1.40233000 -11.01406500 0.37920600 0.37920600 --1.41689000 -7.73079300 0.31355600 0.31355600 --1.42600000 -7.78152600 0.31512300 0.31512300 --1.44440000 -7.88205400 0.31832700 0.31832700 --1.51603000 -8.27411800 0.33055400 0.33055400 --1.65935000 -9.05711100 0.35390500 0.35390500 --1.97292000 -10.76090800 0.40048100 0.40048100 +0.25074000 -7.95485300 0.27197800 0.27197800 +0.25235000 -8.00480100 0.27317300 0.27317300 +0.25568000 -8.10852900 0.27562100 0.27562100 +0.26853000 -8.51046800 0.28487800 0.28487800 +0.29369000 -9.31118800 0.30221800 0.30221800 +0.34617000 -11.04615600 0.33528300 0.33528300 +-0.02810000 -8.01488400 0.27650400 0.27650400 +-0.02823000 -8.06508100 0.27773900 0.27773900 +-0.02855000 -8.16982100 0.28026800 0.28026800 +-0.02978000 -8.57460800 0.28984600 0.28984600 +-0.03273000 -9.38322400 0.30783000 0.30783000 +-0.04109000 -11.13352600 0.34231300 0.34231300 +-0.30835000 -8.03587000 0.28203600 0.28203600 +-0.31024000 -8.08606900 0.28332000 0.28332000 +-0.31422000 -8.19131200 0.28594900 0.28594900 +-0.32961000 -8.59697400 0.29591900 0.29591900 +-0.36085000 -9.40954800 0.31469700 0.31469700 +-0.43046000 -11.16665200 0.35094400 0.35094400 +-0.72840000 -7.99396200 0.29215900 0.29215900 +-0.73290000 -8.04370700 0.29353200 0.29353200 +-0.74239000 -8.14874300 0.29634500 0.29634500 +-0.77898000 -8.55201100 0.30703400 0.30703400 +-0.85277000 -9.36309600 0.32727700 0.32727700 +-1.01431000 -11.11436100 0.36679500 0.36679500 +-1.00621000 -7.91729800 0.30007600 0.30007600 +-1.01245000 -7.96643600 0.30151900 0.30151900 +-1.02559000 -8.07069200 0.30447500 0.30447500 +-1.07618000 -8.46991100 0.31572900 0.31572900 +-1.17820000 -9.27506000 0.33712200 0.33712200 +-1.40064000 -11.01175600 0.37922500 0.37922500 +-1.41624000 -7.73014500 0.31360900 0.31360900 +-1.42501000 -7.77792800 0.31517000 0.31517000 +-1.44356000 -7.88006500 0.31837300 0.31837300 +-1.51482000 -8.26956800 0.33059200 0.33059200 +-1.65861000 -9.05847300 0.35396000 0.35396000 +-1.97108000 -10.75748700 0.40051200 0.40051200 diff --git a/regression/scripts/AVL/test_AVL.py b/regression/scripts/AVL/test_AVL.py index 74c25714ce..2f7226d987 100644 --- a/regression/scripts/AVL/test_AVL.py +++ b/regression/scripts/AVL/test_AVL.py @@ -49,7 +49,7 @@ def main(): configs_analyses = analyses_setup(configs) - run_new_regression = False + run_new_regression = True # append AVL aerodynamic analysis aerodynamics = SUAVE.Analyses.Aerodynamics.AVL() @@ -144,7 +144,7 @@ def main(): # lift coefficient check lift_coefficient = results.segments.cruise.conditions.aerodynamics.lift_coefficient[0][0] - lift_coefficient_true = 0.6123535266221014 + lift_coefficient_true = 0.6124519382551281 print(lift_coefficient) diff_CL = np.abs(lift_coefficient - lift_coefficient_true) @@ -154,7 +154,7 @@ def main(): # moment coefficient check moment_coefficient = results.segments.cruise.conditions.stability.static.CM[0][0] - moment_coefficient_true = -0.6396390695709918 + moment_coefficient_true = -0.6177773381249909 print(moment_coefficient) diff_CM = np.abs(moment_coefficient - moment_coefficient_true) diff --git a/trunk/SUAVE/Analyses/Aerodynamics/AVL_Inviscid.py b/trunk/SUAVE/Analyses/Aerodynamics/AVL_Inviscid.py index 13d9b2e34f..4a237747f8 100644 --- a/trunk/SUAVE/Analyses/Aerodynamics/AVL_Inviscid.py +++ b/trunk/SUAVE/Analyses/Aerodynamics/AVL_Inviscid.py @@ -391,9 +391,11 @@ def evaluate_conditions(self,run_conditions, trim_aircraft ): num_cs = 0 cs_names = [] cs_functions = [] + control_surfaces = False for wing in self.geometry.wings: # this parses through the wings to determine how many control surfaces does the vehicle have if wing.control_surfaces: + control_surfaces = True wing = populate_control_sections (wing) num_cs_on_wing = len(wing.control_surfaces) num_cs += num_cs_on_wing @@ -433,7 +435,7 @@ def evaluate_conditions(self,run_conditions, trim_aircraft ): write_geometry(self,run_script_path) write_mass_file(self,run_conditions) write_run_cases(self,trim_aircraft) - write_input_deck(self, trim_aircraft) + write_input_deck(self, trim_aircraft,control_surfaces) # RUN AVL! results_avl = run_analysis(self) diff --git a/trunk/SUAVE/Analyses/Stability/AVL.py b/trunk/SUAVE/Analyses/Stability/AVL.py index 003e08e12e..bce1363a03 100644 --- a/trunk/SUAVE/Analyses/Stability/AVL.py +++ b/trunk/SUAVE/Analyses/Stability/AVL.py @@ -418,8 +418,10 @@ def evaluate_conditions(self,run_conditions, trim_aircraft ): num_cs = 0 cs_names = [] cs_functions = [] + control_surfaces = False for wing in self.geometry.wings: # this parses through the wings to determine how many control surfaces does the vehicle have if wing.control_surfaces: + control_surfaces = True wing = populate_control_sections(wing) num_cs_on_wing = len(wing.control_surfaces) num_cs += num_cs_on_wing @@ -458,7 +460,7 @@ def evaluate_conditions(self,run_conditions, trim_aircraft ): write_geometry(self,run_script_path) write_mass_file(self,run_conditions) write_run_cases(self,trim_aircraft) - write_input_deck(self, trim_aircraft) + write_input_deck(self, trim_aircraft,control_surfaces) # RUN AVL! results_avl = run_analysis(self) diff --git a/trunk/SUAVE/Methods/Aerodynamics/AVL/write_input_deck.py b/trunk/SUAVE/Methods/Aerodynamics/AVL/write_input_deck.py index 18178d9264..9c23c9e30d 100644 --- a/trunk/SUAVE/Methods/Aerodynamics/AVL/write_input_deck.py +++ b/trunk/SUAVE/Methods/Aerodynamics/AVL/write_input_deck.py @@ -12,7 +12,7 @@ from .purge_files import purge_files ## @ingroup Methods-Aerodynamics-AVL -def write_input_deck(avl_object,trim_aircraft): +def write_input_deck(avl_object,trim_aircraft,control_surfaces): """ This function writes the execution steps used in the AVL call Assumptions: None @@ -54,7 +54,7 @@ def write_input_deck(avl_object,trim_aircraft): input_deck.write(base_input) for case in avl_object.current_status.cases: # write and store aerodynamic and static stability result files - case_command = make_case_command(avl_object,case,trim_aircraft) + case_command = make_case_command(avl_object,case,trim_aircraft,control_surfaces) input_deck.write(case_command) input_deck.write('\nQUIT\n') @@ -62,7 +62,7 @@ def write_input_deck(avl_object,trim_aircraft): return -def make_case_command(avl_object,case,trim_aircraft): +def make_case_command(avl_object,case,trim_aircraft,control_surfaces): """ Makes commands for case execution in AVL Assumptions: None @@ -92,12 +92,17 @@ def make_case_command(avl_object,case,trim_aircraft): {7} {8} {9} -''' - # if trim analysis is specified, this function writes the trim commands +''' + + # if trim analysis is specified, this function writes the trim commands else it + # uses the defined deflection of the control surfaces of the aircraft if trim_aircraft: trim_command = make_trim_text_command(case) else: - trim_command = '' + if control_surfaces: + trim_command = control_surface_deflection_command(case,avl_object) + else: + trim_command = '' index = case.index case_tag = case.tag @@ -187,9 +192,9 @@ def control_surface_deflection_command(case,aircraft): {2}''' cs_idx = 1 cs_commands = '' - for wing in aircraft.wings: + for wing in aircraft.geometry.wings: for ctrl_surf in wing.control_surfaces: - cs_command = cs_template.format(cs_idx,cs_idx,wing.control_surfaces[ctrl_surf].deflection) + cs_command = cs_template.format(cs_idx,cs_idx,ctrl_surf.deflection) cs_commands = cs_commands + cs_command cs_idx += 1 return cs_commands \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Aerodynamics/AVL/write_run_cases.py b/trunk/SUAVE/Methods/Aerodynamics/AVL/write_run_cases.py index 2295d0dfe8..60f71e272f 100644 --- a/trunk/SUAVE/Methods/Aerodynamics/AVL/write_run_cases.py +++ b/trunk/SUAVE/Methods/Aerodynamics/AVL/write_run_cases.py @@ -11,6 +11,7 @@ # Imports # ---------------------------------------------------------------------- from SUAVE.Methods.Aerodynamics.AVL.purge_files import purge_files +from SUAVE.Components.Wings.Control_Surfaces import Aileron , Elevator , Slat , Flap , Rudder ## @ingroup Analyses-AVL def write_run_cases(avl_object,trim_aircraft): @@ -143,7 +144,7 @@ def write_run_cases(avl_object,trim_aircraft): controls = [] if case.stability_and_control.number_control_surfaces != 0 : # write control surface text in .run file if there is any - controls = make_controls_case_text(case.stability_and_control.control_surface_names,case.stability_and_control.control_surface_functions) + controls = make_controls_case_text(case.stability_and_control.control_surface_names,avl_object.geometry) controls_text = ''.join(controls) # write the .run file using template and the extracted vehicle properties and flight condition @@ -153,35 +154,36 @@ def write_run_cases(avl_object,trim_aircraft): return -def make_controls_case_text(cs_names, cs_functions): +def make_controls_case_text(cs_names,avl_aircraft): """ This function writes the text of the control surfaces in the AVL batch analysis. This tells AVL what control surface you want use to control a particular response. """ control_surface_text = [] - for idx in range(len(cs_names)): - # template for control surface - base_control_cond_text = ' {0}-> {1}= 0.00000\n' - - # Get name of control surface - cs_function = cs_functions[idx] - ctrl_tag = cs_names[idx] - # This condition block assigns the control surface to a particular stabiltiy response - if cs_function == 'flap': # if control surface function is 'flap', specify to AVL that it is a flap - ctrl_name = "{:<13}".format(ctrl_tag) - variable = 'flap ' - elif cs_function == 'aileron': # if control surface funcion is 'aileron', specify to AVL that this is used to produce no roll moment - ctrl_name = "{:<13}".format(ctrl_tag) - variable = 'Cl roll mom ' - elif cs_function == 'elevator': # if control surface function is 'elevator', specify to AVL that this is used to produce no pitch moment - ctrl_name = "{:<13}".format(ctrl_tag) - variable = 'Cm pitchmom ' - elif cs_function == 'rudder': # if control surface function is 'rudder', specify to AVL that this is used to produce no yaw moment - ctrl_name = "{:<13}".format(ctrl_tag) - variable = 'Cn yaw mom ' + + for wing in avl_aircraft.wings: + for ctrl_surf in wing.control_surfaces: + if (type(ctrl_surf) == Slat): + pass + else: + # template for control surface + base_control_cond_text = ' {0}-> {1}= 0.00000\n' + # This condition block assigns the control surface to a particular stabiltiy response + if (type(ctrl_surf) == Flap): # if control surface function is 'flap', specify to AVL that it is a flap + ctrl_name = "{:<13}".format(ctrl_surf.tag) + variable = 'flap ' + elif (type(ctrl_surf) == Aileron): # if control surface funcion is 'aileron', specify to AVL that this is used to produce no roll moment + ctrl_name = "{:<13}".format(ctrl_surf.tag) + variable = 'Cl roll mom ' + elif (type(ctrl_surf) == Elevator): # if control surface function is 'elevator', specify to AVL that this is used to produce no pitch moment + ctrl_name = "{:<13}".format(ctrl_surf.tag) + variable = 'Cm pitchmom ' + elif (type(ctrl_surf) == Rudder): # if control surface function is 'rudder', specify to AVL that this is used to produce no yaw moment + ctrl_name = "{:<13}".format(ctrl_surf.tag) + variable = 'Cn yaw mom ' + + # write the control surface functionality into template + text = base_control_cond_text.format(ctrl_name,variable) - # write the control surface functionality into template - text = base_control_cond_text.format(ctrl_name,variable) - - # append text - control_surface_text.append(text) + # append text + control_surface_text.append(text) return control_surface_text From 780731f0c24048bacd07c3fe606d34ceb0a329b2 Mon Sep 17 00:00:00 2001 From: Matthew Clarke Date: Thu, 18 Nov 2021 09:55:08 -0800 Subject: [PATCH 2/2] Update test_AVL.py --- regression/scripts/AVL/test_AVL.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/regression/scripts/AVL/test_AVL.py b/regression/scripts/AVL/test_AVL.py index 2f7226d987..ca0accbb5e 100644 --- a/regression/scripts/AVL/test_AVL.py +++ b/regression/scripts/AVL/test_AVL.py @@ -49,7 +49,7 @@ def main(): configs_analyses = analyses_setup(configs) - run_new_regression = True + run_new_regression = False # append AVL aerodynamic analysis aerodynamics = SUAVE.Analyses.Aerodynamics.AVL()