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Merge d720dea into 979215f
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@mclarke2
mclarke2 committed Feb 28, 2022
2 parents 979215f + d720dea commit 1e1f3fb
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Showing 184 changed files with 1,191 additions and 1,240 deletions.
12 changes: 6 additions & 6 deletions regression/automatic_regression.py
View file
Expand Up @@ -44,13 +44,13 @@
'scripts/aerodynamics/sideslip_and_rotation_vlm.py',
'scripts/airfoil_import/airfoil_import_test.py',
'scripts/airfoil_import/airfoil_interpolation_test.py',
'scripts/airfoil_analysis/airfoil_panel_method_test.py',
'scripts/airfoil_analysis/airfoil_panel_method_test.py',
'scripts/atmosphere/atmosphere.py',
'scripts/atmosphere/constant_temperature.py',
'scripts/AVL/test_AVL.py',
'scripts/B737/mission_B737.py',
'scripts/B737/mission_B737.py',
'scripts/battery/aircraft_discharge_comparisons.py',
'scripts/battery/battery_cell_discharge_tests.py',
'scripts/battery/battery_cell_discharge_tests.py',
'scripts/cmalpha/cmalpha.py',
'scripts/cnbeta/cnbeta.py',
'scripts/concorde/concorde.py',
Expand All @@ -77,10 +77,10 @@
'scripts/mission_range_and_weight_sizing/take_off_weight_from_tofl.py',
'scripts/motor/motor_test.py',
'scripts/multifidelity/optimize_mf.py',
'scripts/noise_optimization/Noise_Test.py',
'scripts/noise_optimization/Noise_Test.py',
'scripts/noise_fidelity_zero/DC_10_noise.py',
'scripts/noise_fidelity_one/propeller_noise.py',
'scripts/noise_fidelity_one/aircraft_noise.py',
'scripts/noise_fidelity_one/propeller_noise.py',
'scripts/noise_fidelity_one/aircraft_noise.py',
'scripts/nonuniform_propeller_inflow/nonuniform_propeller_inflow.py',
'scripts/optimization_packages/optimization_packages.py',
'scripts/payload_range/payload_range.py',
Expand Down
2 changes: 1 addition & 1 deletion regression/scripts/AVL/avl_files/base.avl
View file
Expand Up @@ -7,7 +7,7 @@ cruise
0 0 0.0

#Sref Cref Bref <meters>
124.862 4.235 34.32
124.862 4.4875106307239605 34.32

#Xref Yref Zref <meters>
15.30987849 0.0 -0.48023939
Expand Down
14 changes: 7 additions & 7 deletions regression/scripts/AVL/avl_files/body_axis_derivatives_case_0001_0001.txt
View file
Expand Up @@ -6,7 +6,7 @@
# Strips = 170
# Vortices =1700

Sref = 124.86 Cref = 4.2350 Bref = 34.320
Sref = 124.86 Cref = 4.4875 Bref = 34.320
Xref = 15.310 Yref = 0.0000 Zref =-0.48024

Standard axis orientation, X fwd, Z down
Expand All @@ -18,7 +18,7 @@
Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000

CXtot = 0.00029 Cltot = 0.00000 Cl'tot = 0.00000
CYtot = 0.00000 Cmtot = 0.24765
CYtot = 0.00000 Cmtot = 0.23372
CZtot = 0.04144 Cntot = -0.00000 Cn'tot = -0.00000

CLtot = -0.04142
Expand All @@ -42,16 +42,16 @@
y force CY | CYu = 0.000000 CYv = -0.814064 CYw = -0.000000
z force CZ | CZu = -0.115157 CZv = -0.000000 CZw = -5.672447
x mom. Cl | Clu = 0.000000 Clv = -0.175563 Clw = -0.000001
y mom. Cm | Cmu = 0.217385 Cmv = -0.000000 Cmw = -7.967156
y mom. Cm | Cmu = 0.205153 Cmv = -0.000000 Cmw = -7.518848
z mom. Cn | Cnu = -0.000000 Cnv = 0.278143 Cnw = -0.000000

roll rate p pitch rate q yaw rate r
---------------- ---------------- ----------------
x force CX | CXp = -0.000000 CXq = -1.189839 CXr = 0.000000
x force CX | CXp = -0.000000 CXq = -1.122887 CXr = 0.000000
y force CY | CYp = -0.307407 CYq = -0.000001 CYr = 0.977800
z force CZ | CZp = -0.000001 CZq = -27.112568 CZr = 0.000000
z force CZ | CZp = -0.000001 CZq = -25.586954 CZr = 0.000000
x mom. Cl | Clp = -0.484658 Clq = -0.000003 Clr = 0.167556
y mom. Cm | Cmp = -0.000002 Cmq = -77.735023 Cmr = 0.000000
y mom. Cm | Cmp = -0.000002 Cmq = -69.232903 Cmr = 0.000000
z mom. Cn | Cnp = 0.137539 Cnq = 0.000001 Cnr = -0.513442

slat d1 flap d2 aileron d3 elevator d4
Expand All @@ -60,7 +60,7 @@
y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000363 CYd4 = -0.000000
z force CZ | CZd1 = 0.000145 CZd2 = 0.000000 CZd3 = 0.000000 CZd4 = -0.012032
x mom. Cl | Cld1 = -0.000000 Cld2 = 0.000000 Cld3 = 0.001927 Cld4 = -0.000000
y mom. Cm | Cmd1 = 0.000163 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.058277
y mom. Cm | Cmd1 = 0.000154 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.054998
z mom. Cn | Cnd1 = -0.000000 Cnd2 = 0.000000 Cnd3 = -0.000078 Cnd4 = 0.000000


14 changes: 7 additions & 7 deletions regression/scripts/AVL/avl_files/body_axis_derivatives_case_0001_0002.txt
View file
Expand Up @@ -6,7 +6,7 @@
# Strips = 170
# Vortices =1700

Sref = 124.86 Cref = 4.2350 Bref = 34.320
Sref = 124.86 Cref = 4.4875 Bref = 34.320
Xref = 15.310 Yref = 0.0000 Zref =-0.48024

Standard axis orientation, X fwd, Z down
Expand All @@ -18,7 +18,7 @@
Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000

CXtot = -0.00208 Cltot = -0.00000 Cl'tot = -0.00000
CYtot = 0.00000 Cmtot = -0.03118
CYtot = 0.00000 Cmtot = -0.02942
CZtot = -0.15685 Cntot = -0.00000 Cn'tot = -0.00000

CLtot = 0.15685
Expand All @@ -42,16 +42,16 @@
y force CY | CYu = 0.000000 CYv = -0.820098 CYw = -0.000000
z force CZ | CZu = -0.313695 CZv = -0.000000 CZw = -5.683364
x mom. Cl | Clu = -0.000000 Clv = -0.199739 Clw = -0.000001
y mom. Cm | Cmu = -0.062357 Cmv = -0.000000 Cmw = -8.014535
y mom. Cm | Cmu = -0.058848 Cmv = -0.000000 Cmw = -7.563560
z mom. Cn | Cnu = -0.000000 Cnv = 0.276415 Cnw = -0.000000

roll rate p pitch rate q yaw rate r
---------------- ---------------- ----------------
x force CX | CXp = 0.000000 CXq = -0.196466 CXr = 0.000000
x force CX | CXp = 0.000000 CXq = -0.185411 CXr = 0.000000
y force CY | CYp = -0.237386 CYq = -0.000001 CYr = 0.992449
z force CZ | CZp = -0.000001 CZq = -27.148010 CZr = 0.000000
z force CZ | CZp = -0.000001 CZq = -25.620401 CZr = 0.000000
x mom. Cl | Clp = -0.484302 Clq = -0.000003 Clr = 0.197647
y mom. Cm | Cmp = -0.000002 Cmq = -78.046608 Cmr = 0.000000
y mom. Cm | Cmp = -0.000002 Cmq = -69.510414 Cmr = 0.000000
z mom. Cn | Cnp = 0.093363 Cnq = 0.000000 Cnr = -0.516870

slat d1 flap d2 aileron d3 elevator d4
Expand All @@ -60,7 +60,7 @@
y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000340 CYd4 = -0.000000
z force CZ | CZd1 = 0.000148 CZd2 = 0.000000 CZd3 = 0.000000 CZd4 = -0.012033
x mom. Cl | Cld1 = -0.000000 Cld2 = 0.000000 Cld3 = 0.001924 Cld4 = -0.000000
y mom. Cm | Cmd1 = 0.000178 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.058336
y mom. Cm | Cmd1 = 0.000168 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.055053
z mom. Cn | Cnd1 = 0.000000 Cnd2 = 0.000000 Cnd3 = -0.000043 Cnd4 = 0.000000


14 changes: 7 additions & 7 deletions regression/scripts/AVL/avl_files/body_axis_derivatives_case_0001_0003.txt
View file
Expand Up @@ -6,7 +6,7 @@
# Strips = 170
# Vortices =1700

Sref = 124.86 Cref = 4.2350 Bref = 34.320
Sref = 124.86 Cref = 4.4875 Bref = 34.320
Xref = 15.310 Yref = 0.0000 Zref =-0.48024

Standard axis orientation, X fwd, Z down
Expand All @@ -18,7 +18,7 @@
Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000

CXtot = 0.00620 Cltot = -0.00000 Cl'tot = -0.00000
CYtot = 0.00000 Cmtot = -0.31141
CYtot = 0.00000 Cmtot = -0.29389
CZtot = -0.35501 Cntot = -0.00000 Cn'tot = -0.00000

CLtot = 0.35501
Expand All @@ -42,16 +42,16 @@
y force CY | CYu = 0.000000 CYv = -0.825133 CYw = -0.000000
z force CZ | CZu = -0.511850 CZv = -0.000000 CZw = -5.687358
x mom. Cl | Clu = -0.000000 Clv = -0.223673 Clw = -0.000001
y mom. Cm | Cmu = -0.342022 Cmv = -0.000000 Cmw = -8.052149
y mom. Cm | Cmu = -0.322776 Cmv = -0.000000 Cmw = -7.599057
z mom. Cn | Cnu = -0.000000 Cnv = 0.274350 Cnw = -0.000000

roll rate p pitch rate q yaw rate r
---------------- ---------------- ----------------
x force CX | CXp = 0.000000 CXq = 0.797146 CXr = 0.000000
x force CX | CXp = 0.000000 CXq = 0.752291 CXr = 0.000000
y force CY | CYp = -0.167077 CYq = -0.000001 CYr = 1.005889
z force CZ | CZp = -0.000001 CZq = -27.150375 CZr = 0.000000
z force CZ | CZp = -0.000001 CZq = -25.622633 CZr = 0.000000
x mom. Cl | Clp = -0.483356 Clq = -0.000003 Clr = 0.227497
y mom. Cm | Cmp = -0.000002 Cmq = -78.263100 Cmr = 0.000000
y mom. Cm | Cmp = -0.000002 Cmq = -69.703224 Cmr = 0.000000
z mom. Cn | Cnp = 0.049073 Cnq = 0.000000 Cnr = -0.519668

slat d1 flap d2 aileron d3 elevator d4
Expand All @@ -60,7 +60,7 @@
y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000315 CYd4 = -0.000000
z force CZ | CZd1 = 0.000152 CZd2 = 0.000000 CZd3 = 0.000000 CZd4 = -0.012004
x mom. Cl | Cld1 = -0.000000 Cld2 = 0.000000 Cld3 = 0.001916 Cld4 = -0.000000
y mom. Cm | Cmd1 = 0.000193 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.058251
y mom. Cm | Cmd1 = 0.000182 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.054973
z mom. Cn | Cnd1 = 0.000000 Cnd2 = 0.000000 Cnd3 = -0.000009 Cnd4 = 0.000000


14 changes: 7 additions & 7 deletions regression/scripts/AVL/avl_files/body_axis_derivatives_case_0001_0004.txt
View file
Expand Up @@ -6,7 +6,7 @@
# Strips = 170
# Vortices =1700

Sref = 124.86 Cref = 4.2350 Bref = 34.320
Sref = 124.86 Cref = 4.4875 Bref = 34.320
Xref = 15.310 Yref = 0.0000 Zref =-0.48024

Standard axis orientation, X fwd, Z down
Expand All @@ -18,7 +18,7 @@
Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000

CXtot = 0.03848 Cltot = -0.00000 Cl'tot = -0.00000
CYtot = 0.00000 Cmtot = -0.73142
CYtot = 0.00000 Cmtot = -0.69026
CZtot = -0.64992 Cntot = -0.00000 Cn'tot = -0.00000

CLtot = 0.65080
Expand All @@ -42,16 +42,16 @@
y force CY | CYu = -0.000000 CYv = -0.830799 CYw = 0.000000
z force CZ | CZu = -0.807839 CZv = -0.000000 CZw = -5.680357
x mom. Cl | Clu = -0.000000 Clv = -0.259052 Clw = -0.000001
y mom. Cm | Cmu = -0.760632 Cmv = -0.000000 Cmw = -8.090164
y mom. Cm | Cmu = -0.717831 Cmv = -0.000000 Cmw = -7.634933
z mom. Cn | Cnu = -0.000000 Cnv = 0.270628 Cnw = -0.000000

roll rate p pitch rate q yaw rate r
---------------- ---------------- ----------------
x force CX | CXp = 0.000000 CXq = 2.285366 CXr = 0.000000
x force CX | CXp = 0.000000 CXq = 2.156769 CXr = 0.000000
y force CY | CYp = -0.061257 CYq = -0.000001 CYr = 1.023746
z force CZ | CZp = -0.000001 CZq = -27.091915 CZr = 0.000000
z force CZ | CZp = -0.000001 CZq = -25.567463 CZr = 0.000000
x mom. Cl | Clp = -0.480833 Clq = -0.000003 Clr = 0.271741
y mom. Cm | Cmp = -0.000002 Cmq = -78.408997 Cmr = 0.000001
y mom. Cm | Cmp = -0.000002 Cmq = -69.833176 Cmr = 0.000001
z mom. Cn | Cnp = -0.017458 Cnq = 0.000000 Cnr = -0.522678

slat d1 flap d2 aileron d3 elevator d4
Expand All @@ -60,7 +60,7 @@
y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000278 CYd4 = -0.000000
z force CZ | CZd1 = 0.000156 CZd2 = 0.000000 CZd3 = 0.000000 CZd4 = -0.011907
x mom. Cl | Cld1 = -0.000000 Cld2 = 0.000000 Cld3 = 0.001895 Cld4 = -0.000000
y mom. Cm | Cmd1 = 0.000215 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.057859
y mom. Cm | Cmd1 = 0.000202 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.054603
z mom. Cn | Cnd1 = 0.000000 Cnd2 = 0.000000 Cnd3 = 0.000042 Cnd4 = 0.000000


14 changes: 7 additions & 7 deletions regression/scripts/AVL/avl_files/body_axis_derivatives_case_0001_0005.txt
View file
Expand Up @@ -6,7 +6,7 @@
# Strips = 170
# Vortices =1700

Sref = 124.86 Cref = 4.2350 Bref = 34.320
Sref = 124.86 Cref = 4.4875 Bref = 34.320
Xref = 15.310 Yref = 0.0000 Zref =-0.48024

Standard axis orientation, X fwd, Z down
Expand All @@ -18,7 +18,7 @@
Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000

CXtot = 0.07308 Cltot = -0.00000 Cl'tot = -0.00000
CYtot = 0.00000 Cmtot = -1.00920
CYtot = 0.00000 Cmtot = -0.95242
CZtot = -0.84357 Cntot = -0.00000 Cn'tot = -0.00000

CLtot = 0.84619
Expand All @@ -42,16 +42,16 @@
y force CY | CYu = -0.000000 CYv = -0.833312 CYw = -0.000000
z force CZ | CZu = -1.003985 CZv = -0.000000 CZw = -5.667037
x mom. Cl | Clu = -0.000000 Clv = -0.282250 Clw = -0.000001
y mom. Cm | Cmu = -1.038618 Cmv = -0.000000 Cmw = -8.103190
y mom. Cm | Cmu = -0.980175 Cmv = -0.000000 Cmw = -7.647227
z mom. Cn | Cnu = -0.000000 Cnv = 0.267733 Cnw = -0.000000

roll rate p pitch rate q yaw rate r
---------------- ---------------- ----------------
x force CX | CXp = 0.000000 CXq = 3.274284 CXr = 0.000000
x force CX | CXp = 0.000000 CXq = 3.090041 CXr = 0.000000
y force CY | CYp = 0.009401 CYq = -0.000000 CYr = 1.034094
z force CZ | CZp = -0.000001 CZq = -27.011665 CZr = 0.000000
z force CZ | CZp = -0.000001 CZq = -25.491730 CZr = 0.000000
x mom. Cl | Clp = -0.478418 Clq = -0.000003 Clr = 0.300831
y mom. Cm | Cmp = -0.000002 Cmq = -78.386871 Cmr = 0.000001
y mom. Cm | Cmp = -0.000002 Cmq = -69.813461 Cmr = 0.000001
z mom. Cn | Cnp = -0.061796 Cnq = -0.000000 Cnr = -0.523889

slat d1 flap d2 aileron d3 elevator d4
Expand All @@ -60,7 +60,7 @@
y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000252 CYd4 = -0.000000
z force CZ | CZd1 = 0.000158 CZd2 = 0.000000 CZd3 = 0.000000 CZd4 = -0.011806
x mom. Cl | Cld1 = -0.000000 Cld2 = 0.000000 Cld3 = 0.001875 Cld4 = -0.000000
y mom. Cm | Cmd1 = 0.000228 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.057422
y mom. Cm | Cmd1 = 0.000215 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.054190
z mom. Cn | Cnd1 = 0.000000 Cnd2 = 0.000000 Cnd3 = 0.000076 Cnd4 = 0.000000


14 changes: 7 additions & 7 deletions regression/scripts/AVL/avl_files/body_axis_derivatives_case_0001_0006.txt
View file
Expand Up @@ -6,7 +6,7 @@
# Strips = 170
# Vortices =1700

Sref = 124.86 Cref = 4.2350 Bref = 34.320
Sref = 124.86 Cref = 4.4875 Bref = 34.320
Xref = 15.310 Yref = 0.0000 Zref =-0.48024

Standard axis orientation, X fwd, Z down
Expand All @@ -18,7 +18,7 @@
Mach = 0.050 rb/2V = 0.00000 r'b/2V = 0.00000

CXtot = 0.14419 Cltot = -0.00000 Cl'tot = -0.00000
CYtot = 0.00000 Cmtot = -1.41916
CYtot = 0.00000 Cmtot = -1.33931
CZtot = -1.12725 Cntot = -0.00000 Cn'tot = 0.00000

CLtot = 1.13516
Expand All @@ -42,16 +42,16 @@
y force CY | CYu = 0.000000 CYv = -0.835177 CYw = 0.000000
z force CZ | CZu = -1.295835 CZv = -0.000000 CZw = -5.634119
x mom. Cl | Clu = -0.000000 Clv = -0.316394 Clw = -0.000001
y mom. Cm | Cmu = -1.453119 Cmv = -0.000000 Cmw = -8.104220
y mom. Cm | Cmu = -1.371352 Cmv = -0.000000 Cmw = -7.648198
z mom. Cn | Cnu = -0.000000 Cnv = 0.262781 Cnw = -0.000000

roll rate p pitch rate q yaw rate r
---------------- ---------------- ----------------
x force CX | CXp = 0.000000 CXq = 4.749805 CXr = 0.000000
x force CX | CXp = 0.000000 CXq = 4.482535 CXr = 0.000000
y force CY | CYp = 0.115339 CYq = -0.000001 CYr = 1.047251
z force CZ | CZp = -0.000001 CZq = -26.829632 CZr = 0.000000
z force CZ | CZp = -0.000001 CZq = -25.319939 CZr = 0.000000
x mom. Cl | Clp = -0.473704 Clq = -0.000003 Clr = 0.343767
y mom. Cm | Cmp = -0.000002 Cmq = -78.174652 Cmr = 0.000001
y mom. Cm | Cmp = -0.000002 Cmq = -69.624458 Cmr = 0.000001
z mom. Cn | Cnp = -0.128145 Cnq = 0.000000 Cnr = -0.524508

slat d1 flap d2 aileron d3 elevator d4
Expand All @@ -60,7 +60,7 @@
y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000213 CYd4 = -0.000000
z force CZ | CZd1 = 0.000161 CZd2 = 0.000000 CZd3 = 0.000000 CZd4 = -0.011602
x mom. Cl | Cld1 = -0.000000 Cld2 = 0.000000 Cld3 = 0.001837 Cld4 = -0.000000
y mom. Cm | Cmd1 = 0.000248 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.056508
y mom. Cm | Cmd1 = 0.000234 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.053328
z mom. Cn | Cnd1 = 0.000000 Cnd2 = 0.000000 Cnd3 = 0.000125 Cnd4 = 0.000000


14 changes: 7 additions & 7 deletions regression/scripts/AVL/avl_files/body_axis_derivatives_case_0002_0001.txt
View file
Expand Up @@ -6,7 +6,7 @@
# Strips = 170
# Vortices =1700

Sref = 124.86 Cref = 4.2350 Bref = 34.320
Sref = 124.86 Cref = 4.4875 Bref = 34.320
Xref = 15.310 Yref = 0.0000 Zref =-0.48024

Standard axis orientation, X fwd, Z down
Expand All @@ -18,7 +18,7 @@
Mach = 0.150 rb/2V = 0.00000 r'b/2V = 0.00000

CXtot = 0.00028 Cltot = 0.00000 Cl'tot = 0.00000
CYtot = 0.00000 Cmtot = 0.24926
CYtot = 0.00000 Cmtot = 0.23523
CZtot = 0.04163 Cntot = -0.00000 Cn'tot = -0.00000

CLtot = -0.04161
Expand All @@ -42,16 +42,16 @@
y force CY | CYu = 0.000000 CYv = -0.816259 CYw = -0.000000
z force CZ | CZu = -0.116008 CZv = -0.000000 CZw = -5.707551
x mom. Cl | Clu = -0.000000 Clv = -0.176335 Clw = -0.000001
y mom. Cm | Cmu = 0.218851 Cmv = -0.000000 Cmw = -8.017196
y mom. Cm | Cmu = 0.206536 Cmv = -0.000000 Cmw = -7.566070
z mom. Cn | Cnu = -0.000000 Cnv = 0.279364 Cnw = 0.000000

roll rate p pitch rate q yaw rate r
---------------- ---------------- ----------------
x force CX | CXp = -0.000000 CXq = -1.195905 CXr = 0.000000
x force CX | CXp = -0.000000 CXq = -1.128612 CXr = 0.000000
y force CY | CYp = -0.308344 CYq = -0.000001 CYr = 0.980680
z force CZ | CZp = -0.000001 CZq = -27.267969 CZr = 0.000000
z force CZ | CZp = -0.000001 CZq = -25.733610 CZr = 0.000000
x mom. Cl | Clp = -0.487267 Clq = -0.000003 Clr = 0.168243
y mom. Cm | Cmp = -0.000002 Cmq = -78.167221 Cmr = 0.000000
y mom. Cm | Cmp = -0.000002 Cmq = -69.617844 Cmr = 0.000000
z mom. Cn | Cnp = 0.137896 Cnq = 0.000000 Cnr = -0.515152

slat d1 flap d2 aileron d3 elevator d4
Expand All @@ -60,7 +60,7 @@
y force CY | CYd1 = -0.000000 CYd2 = 0.000000 CYd3 = 0.000365 CYd4 = -0.000000
z force CZ | CZd1 = 0.000146 CZd2 = 0.000000 CZd3 = 0.000000 CZd4 = -0.012103
x mom. Cl | Cld1 = -0.000000 Cld2 = 0.000000 Cld3 = 0.001938 Cld4 = -0.000000
y mom. Cm | Cmd1 = 0.000164 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.058650
y mom. Cm | Cmd1 = 0.000155 Cmd2 = 0.000000 Cmd3 = 0.000000 Cmd4 = -0.055349
z mom. Cn | Cnd1 = -0.000000 Cnd2 = 0.000000 Cnd3 = -0.000078 Cnd4 = 0.000000


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