From 1ac5fa6b047e8fbad14f91a8ef56a17570804ddc Mon Sep 17 00:00:00 2001 From: WalterMaier Date: Mon, 16 Apr 2018 11:11:05 -0700 Subject: [PATCH 1/6] github sucks --- regression/scripts/AVL/avl_files/aircraft.avl | 167 ++++++++ .../scripts/AVL/avl_files/batch_001.run | 258 ++++++++++++ .../scripts/AVL/avl_files/batch_002.run | 258 ++++++++++++ .../scripts/AVL/avl_files/batch_003.run | 258 ++++++++++++ .../scripts/AVL/avl_files/batch_004.run | 258 ++++++++++++ .../scripts/AVL/avl_files/batch_005.run | 258 ++++++++++++ .../scripts/AVL/avl_files/batch_006.run | 258 ++++++++++++ .../scripts/AVL/avl_files/commands_001.deck | 29 ++ .../scripts/AVL/avl_files/commands_002.deck | 29 ++ .../scripts/AVL/avl_files/commands_003.deck | 29 ++ .../scripts/AVL/avl_files/commands_004.deck | 29 ++ .../scripts/AVL/avl_files/commands_005.deck | 29 ++ .../scripts/AVL/avl_files/commands_006.deck | 29 ++ .../AVL/avl_files/results_case_001_01.txt | 53 +++ .../AVL/avl_files/results_case_001_02.txt | 53 +++ 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.../Correlations/General_Aviation/payload.py | 52 +++ .../Correlations/General_Aviation/systems.py | 90 +++++ .../General_Aviation/tail_horizontal.py | 50 +++ .../General_Aviation/tail_vertical.py | 65 +++ .../General_Aviation/wing_main.py | 53 +++ .../integrated_propulsion_general_aviation.py | 38 ++ 59 files changed, 4647 insertions(+) create mode 100644 regression/scripts/AVL/avl_files/aircraft.avl create mode 100644 regression/scripts/AVL/avl_files/batch_001.run create mode 100644 regression/scripts/AVL/avl_files/batch_002.run create mode 100644 regression/scripts/AVL/avl_files/batch_003.run create mode 100644 regression/scripts/AVL/avl_files/batch_004.run create mode 100644 regression/scripts/AVL/avl_files/batch_005.run create mode 100644 regression/scripts/AVL/avl_files/batch_006.run create mode 100644 regression/scripts/AVL/avl_files/commands_001.deck create mode 100644 regression/scripts/AVL/avl_files/commands_002.deck create mode 100644 regression/scripts/AVL/avl_files/commands_003.deck create mode 100644 regression/scripts/AVL/avl_files/commands_004.deck create mode 100644 regression/scripts/AVL/avl_files/commands_005.deck create mode 100644 regression/scripts/AVL/avl_files/commands_006.deck create mode 100644 regression/scripts/AVL/avl_files/results_case_001_01.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_001_02.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_001_03.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_001_04.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_001_05.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_001_06.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_002_01.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_002_02.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_002_03.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_002_04.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_002_05.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_002_06.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_003_01.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_003_02.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_003_03.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_003_04.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_003_05.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_003_06.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_004_01.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_004_02.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_004_03.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_004_04.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_004_05.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_004_06.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_005_01.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_005_02.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_005_03.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_005_04.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_005_05.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_005_06.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_006_01.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_006_02.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_006_03.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_006_04.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_006_05.txt create mode 100644 regression/scripts/AVL/avl_files/results_case_006_06.txt create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/__init__.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/fuselage.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/landing_gear.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/systems.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_horizontal.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_vertical.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py create mode 100644 trunk/SUAVE/Methods/Weights/Correlations/Propulsion/integrated_propulsion_general_aviation.py diff --git a/regression/scripts/AVL/avl_files/aircraft.avl b/regression/scripts/AVL/avl_files/aircraft.avl new file mode 100644 index 0000000000..94aa467696 --- /dev/null +++ b/regression/scripts/AVL/avl_files/aircraft.avl @@ -0,0 +1,167 @@ +cruise +#Mach + 0.0 +#Iysym IZsym Zsym + 0 0 0.0 + +#Sref Cref Bref +124.862 4.235 34.32 + +#Xref Yref Zref +15.30987849 0.0 -0.48023939 + + + +#--------------------------------------------------------- +SURFACE +horizontal_stabilizer +#Nchordwise Cspace Nspanwise Sspace +20 1.0 11.0 1.0 + +YDUPLICATE +0.0 + + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +32.83 0 1.14 4.7 0.0523598775598 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +38.7876073814 7.1 1.14 0.955 0.0523598775598 + + +#--------------------------------------------------------- +SURFACE +main_wing +#Nchordwise Cspace Nspanwise Sspace +20 1.0 26.0 1.0 + +YDUPLICATE +0.0 + + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +13.61 0 -1.27 7.76 0.0698131700798 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +21.6118394139 17.16 -1.27 0.782 0.0 + + +#--------------------------------------------------------- +SURFACE +vertical_stabilizer +#Nchordwise Cspace Nspanwise Sspace +20 1.0 12.0 -1.1 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +28.79 0 1.54 8.19 0.0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +32.4164746575 0.0 7.777 0.95 0.0 + + +#--------------------------------------------------------- +SURFACE +fuselage_horizontal +#Nchordwise Cspace Nspanwise Sspace +20 1.0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +6.4 -1.87 0 23.62 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +3.64612038251 -1.496 0 29.5714001643 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +2.19436817059 -1.122 0 32.8478236524 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +1.14076771669 -0.748 0 35.2773803711 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +0.392464413565 -0.374 0 37.0465209103 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +0.0 0.0 0 38.02 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +0.392464413565 0.374 0 37.0465209103 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +1.14076771669 0.748 0 35.2773803711 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +2.19436817059 1.122 0 32.8478236524 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +3.64612038251 1.496 0 29.5714001643 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +6.4 1.87 0 23.62 0.0 1 0 + + +#--------------------------------------------------------- +SURFACE +fuselage_vertical +#Nchordwise Cspace Nspanwise Sspace +20 1.0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +6.4 0 -1.87 23.62 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +3.64612038251 0 -1.496 29.5714001643 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +2.19436817059 0 -1.122 32.8478236524 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +1.14076771669 0 -0.748 35.2773803711 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +0.392464413565 0 -0.374 37.0465209103 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +0.0 0 0.0 38.02 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +0.392464413565 0 0.374 37.0465209103 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +1.14076771669 0 0.748 35.2773803711 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +2.19436817059 0 1.122 32.8478236524 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +3.64612038251 0 1.496 29.5714001643 0.0 1 0 + +SECTION +#Xle Yle Zle Chord Ainc Nspanwise Sspace +6.4 0 1.87 23.62 0.0 1 0 diff --git a/regression/scripts/AVL/avl_files/batch_001.run b/regression/scripts/AVL/avl_files/batch_001.run new file mode 100644 index 0000000000..7605df9783 --- /dev/null +++ b/regression/scripts/AVL/avl_files/batch_001.run @@ -0,0 +1,258 @@ + + + --------------------------------------------- + Run case 1: case_001_01 + + alpha -> alpha = -2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.05 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 2: case_001_02 + + alpha -> alpha = 0.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.05 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 3: case_001_03 + + alpha -> alpha = 2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.05 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 4: case_001_04 + + alpha -> alpha = 5.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.05 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 5: case_001_05 + + alpha -> alpha = 7.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.05 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 6: case_001_06 + + alpha -> alpha = 10.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.05 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + diff --git a/regression/scripts/AVL/avl_files/batch_002.run b/regression/scripts/AVL/avl_files/batch_002.run new file mode 100644 index 0000000000..cb01478d76 --- /dev/null +++ b/regression/scripts/AVL/avl_files/batch_002.run @@ -0,0 +1,258 @@ + + + --------------------------------------------- + Run case 1: case_002_01 + + alpha -> alpha = -2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.15 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 2: case_002_02 + + alpha -> alpha = 0.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.15 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 3: case_002_03 + + alpha -> alpha = 2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.15 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 4: case_002_04 + + alpha -> alpha = 5.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.15 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 5: case_002_05 + + alpha -> alpha = 7.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.15 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 6: case_002_06 + + alpha -> alpha = 10.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.15 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + diff --git a/regression/scripts/AVL/avl_files/batch_003.run b/regression/scripts/AVL/avl_files/batch_003.run new file mode 100644 index 0000000000..4f5924b948 --- /dev/null +++ b/regression/scripts/AVL/avl_files/batch_003.run @@ -0,0 +1,258 @@ + + + --------------------------------------------- + Run case 1: case_003_01 + + alpha -> alpha = -2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.25 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 2: case_003_02 + + alpha -> alpha = 0.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.25 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 3: case_003_03 + + alpha -> alpha = 2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.25 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 4: case_003_04 + + alpha -> alpha = 5.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.25 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 5: case_003_05 + + alpha -> alpha = 7.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.25 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 6: case_003_06 + + alpha -> alpha = 10.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.25 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + diff --git a/regression/scripts/AVL/avl_files/batch_004.run b/regression/scripts/AVL/avl_files/batch_004.run new file mode 100644 index 0000000000..b7e9743070 --- /dev/null +++ b/regression/scripts/AVL/avl_files/batch_004.run @@ -0,0 +1,258 @@ + + + --------------------------------------------- + Run case 1: case_004_01 + + alpha -> alpha = -2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.45 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 2: case_004_02 + + alpha -> alpha = 0.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.45 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 3: case_004_03 + + alpha -> alpha = 2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.45 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 4: case_004_04 + + alpha -> alpha = 5.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.45 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 5: case_004_05 + + alpha -> alpha = 7.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.45 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 6: case_004_06 + + alpha -> alpha = 10.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.45 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + diff --git a/regression/scripts/AVL/avl_files/batch_005.run b/regression/scripts/AVL/avl_files/batch_005.run new file mode 100644 index 0000000000..55a238126d --- /dev/null +++ b/regression/scripts/AVL/avl_files/batch_005.run @@ -0,0 +1,258 @@ + + + --------------------------------------------- + Run case 1: case_005_01 + + alpha -> alpha = -2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.65 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 2: case_005_02 + + alpha -> alpha = 0.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.65 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 3: case_005_03 + + alpha -> alpha = 2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.65 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 4: case_005_04 + + alpha -> alpha = 5.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.65 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 5: case_005_05 + + alpha -> alpha = 7.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.65 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 6: case_005_06 + + alpha -> alpha = 10.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.65 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + diff --git a/regression/scripts/AVL/avl_files/batch_006.run b/regression/scripts/AVL/avl_files/batch_006.run new file mode 100644 index 0000000000..c4b7934ee3 --- /dev/null +++ b/regression/scripts/AVL/avl_files/batch_006.run @@ -0,0 +1,258 @@ + + + --------------------------------------------- + Run case 1: case_006_01 + + alpha -> alpha = -2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.85 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 2: case_006_02 + + alpha -> alpha = 0.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.85 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 3: case_006_03 + + alpha -> alpha = 2.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.85 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 4: case_006_04 + + alpha -> alpha = 5.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.85 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 5: case_006_05 + + alpha -> alpha = 7.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.85 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + + + + --------------------------------------------- + Run case 6: case_006_06 + + alpha -> alpha = 10.0 + beta -> beta = 0 + pb/2V -> pb/2V = 0.00000 + qc/2V -> qc/2V = 0.00000 + rb/2V -> rb/2V = 0.00000 + + + alpha = 0.00000 deg + beta = 0.00000 deg + pb/2V = 0.00000 + qc/2V = 0.00000 + rb/2V = 0.00000 + CL = 0.00000 + CDo = 0.00000 + bank = 0.00000 deg + elevation = 0.00000 deg + heading = 0.00000 deg + Mach = 0.85 + velocity = 0.0000 m/s + density = 0 kg/m^3 + grav.acc. = 9.81 m/s^2 + turn_rad. = 0.00000 m + load_fac. = 0.00000 + X_cg = 15.30987849 m + Y_cg = 0.0 m + Z_cg = -0.48023939 m + mass = 0 kg + Ixx = 0.0 kg-m^2 + Iyy = 0.0 kg-m^2 + Izz = 0.0 kg-m^2 + Ixy = 0.0 kg-m^2 + Iyz = 0.0 kg-m^2 + Izx = 0.0 kg-m^2 + visc CL_a = 0.00000 + visc CL_u = 0.00000 + visc CM_a = 0.00000 + visc CM_u = 0.00000 + diff --git a/regression/scripts/AVL/avl_files/commands_001.deck b/regression/scripts/AVL/avl_files/commands_001.deck new file mode 100644 index 0000000000..4860e158b7 --- /dev/null +++ b/regression/scripts/AVL/avl_files/commands_001.deck @@ -0,0 +1,29 @@ +CASE batch_001.run +OPER +1 +x +st +results_case_001_01.txt +2 +x +st +results_case_001_02.txt +3 +x +st +results_case_001_03.txt +4 +x +st +results_case_001_04.txt +5 +x +st +results_case_001_05.txt +6 +x +st +results_case_001_06.txt + + +QUIT diff --git a/regression/scripts/AVL/avl_files/commands_002.deck b/regression/scripts/AVL/avl_files/commands_002.deck new file mode 100644 index 0000000000..4e5c1bd688 --- /dev/null +++ b/regression/scripts/AVL/avl_files/commands_002.deck @@ -0,0 +1,29 @@ +CASE batch_002.run +OPER +1 +x +st +results_case_002_01.txt +2 +x +st +results_case_002_02.txt +3 +x +st +results_case_002_03.txt +4 +x +st +results_case_002_04.txt +5 +x +st +results_case_002_05.txt +6 +x +st +results_case_002_06.txt + + +QUIT diff --git a/regression/scripts/AVL/avl_files/commands_003.deck b/regression/scripts/AVL/avl_files/commands_003.deck new file mode 100644 index 0000000000..937e9ba4aa --- /dev/null +++ b/regression/scripts/AVL/avl_files/commands_003.deck @@ -0,0 +1,29 @@ +CASE batch_003.run +OPER +1 +x +st +results_case_003_01.txt +2 +x +st +results_case_003_02.txt +3 +x +st +results_case_003_03.txt +4 +x +st +results_case_003_04.txt +5 +x +st +results_case_003_05.txt +6 +x +st +results_case_003_06.txt + + +QUIT diff --git a/regression/scripts/AVL/avl_files/commands_004.deck b/regression/scripts/AVL/avl_files/commands_004.deck new file mode 100644 index 0000000000..2ab1cf5bb7 --- /dev/null +++ b/regression/scripts/AVL/avl_files/commands_004.deck @@ -0,0 +1,29 @@ +CASE batch_004.run +OPER +1 +x +st +results_case_004_01.txt +2 +x +st +results_case_004_02.txt +3 +x +st +results_case_004_03.txt +4 +x +st +results_case_004_04.txt +5 +x +st +results_case_004_05.txt +6 +x +st +results_case_004_06.txt + + +QUIT diff --git a/regression/scripts/AVL/avl_files/commands_005.deck b/regression/scripts/AVL/avl_files/commands_005.deck new file mode 100644 index 0000000000..319378557f --- /dev/null +++ b/regression/scripts/AVL/avl_files/commands_005.deck @@ -0,0 +1,29 @@ +CASE batch_005.run +OPER +1 +x +st +results_case_005_01.txt +2 +x +st +results_case_005_02.txt +3 +x +st +results_case_005_03.txt +4 +x +st +results_case_005_04.txt +5 +x +st +results_case_005_05.txt +6 +x +st +results_case_005_06.txt + + +QUIT diff --git a/regression/scripts/AVL/avl_files/commands_006.deck b/regression/scripts/AVL/avl_files/commands_006.deck new file mode 100644 index 0000000000..7700af236d --- /dev/null +++ b/regression/scripts/AVL/avl_files/commands_006.deck @@ -0,0 +1,29 @@ +CASE batch_006.run +OPER +1 +x +st +results_case_006_01.txt +2 +x +st +results_case_006_02.txt +3 +x +st +results_case_006_03.txt +4 +x +st +results_case_006_04.txt +5 +x +st +results_case_006_05.txt +6 +x +st +results_case_006_06.txt + + +QUIT diff --git a/regression/scripts/AVL/avl_files/results_case_001_01.txt b/regression/scripts/AVL/avl_files/results_case_001_01.txt new file mode 100644 index 0000000000..398428452f --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_001_01.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_001_01 + + 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 = 0.00572 Cltot = 0.00035 Cl'tot = 0.00039 + CYtot = 0.00259 Cmtot = 0.23227 + CZtot = 0.21327 Cntot = -0.00119 Cn'tot = -0.00118 + + CLtot = -0.21334 + CDtot = 0.00172 + CDvis = 0.00000 CDind = 0.0017233 + CLff = -0.21337 CDff = 0.0017492 | Trefftz + CYff = 0.00267 e = 0.8784 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.291620 CLb = 0.086240 + y force CY | CYa = -0.071018 CYb = -0.599244 + x' mom. Cl'| Cla = -0.012239 Clb = -0.035714 + y mom. Cm | Cma = -6.850778 Cmb = -0.290903 + z' mom. Cn'| Cna = 0.031634 Cnb = 0.122179 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.019270 CLq = 26.943369 CLr = -0.094332 + y force CY | CYp = -0.140089 CYq = -0.794603 CYr = 0.645785 + x' mom. Cl'| Clp = -0.494144 Clq = -0.120991 Clr = 0.024145 + y mom. Cm | Cmp = -0.066784 Cmq = -73.075294 Cmr = 0.323890 + z' mom. Cn'| Cnp = 0.064770 Cnq = 0.361345 Cnr = -0.284176 + + Neutral point Xnp = 19.921257 + + Clb Cnr / Clr Cnb = 3.440398 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_001_02.txt b/regression/scripts/AVL/avl_files/results_case_001_02.txt new file mode 100644 index 0000000000..fce977470f --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_001_02.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_001_02 + + 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 = -0.00000 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00003 Cmtot = -0.00655 + CZtot = -0.00647 Cntot = -0.00001 Cn'tot = -0.00001 + + CLtot = 0.00647 + CDtot = 0.00000 + CDvis = 0.00000 CDind = 0.0000017 + CLff = 0.00647 CDff = 0.0000016 | Trefftz + CYff = 0.00003 e = 0.8828 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.299140 CLb = 0.084708 + y force CY | CYa = -0.075666 CYb = -0.612077 + x' mom. Cl'| Cla = -0.009928 Clb = -0.054975 + y mom. Cm | Cma = -6.827147 Cmb = -0.287667 + z' mom. Cn'| Cna = 0.035061 Cnb = 0.130543 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.016026 CLq = 27.005331 CLr = -0.093130 + y force CY | CYp = -0.060244 CYq = -0.834286 CYr = 0.664705 + x' mom. Cl'| Clp = -0.491201 Clq = -0.106989 Clr = 0.061530 + y mom. Cm | Cmp = -0.056506 Cmq = -73.156754 Cmr = 0.321322 + z' mom. Cn'| Cnp = 0.032431 Cnq = 0.389551 Cnr = -0.295398 + + Neutral point Xnp = 19.899864 + + Clb Cnr / Clr Cnb = 2.021784 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_001_03.txt b/regression/scripts/AVL/avl_files/results_case_001_03.txt new file mode 100644 index 0000000000..d69572294c --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_001_03.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_001_03 + + 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 = 0.00596 Cltot = -0.00034 Cl'tot = -0.00030 + CYtot = -0.00269 Cmtot = -0.24397 + CZtot = -0.22614 Cntot = 0.00125 Cn'tot = 0.00126 + + CLtot = 0.22621 + CDtot = 0.00193 + CDvis = 0.00000 CDind = 0.0019335 + CLff = 0.22630 CDff = 0.0019564 | Trefftz + CYff = -0.00261 e = 0.8834 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.288028 CLb = 0.083164 + y force CY | CYa = -0.079945 CYb = -0.624165 + x' mom. Cl'| Cla = -0.007262 Clb = -0.073607 + y mom. Cm | Cma = -6.770255 Cmb = -0.284079 + z' mom. Cn'| Cna = 0.038185 Cnb = 0.140231 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.012885 CLq = 27.063635 CLr = -0.091774 + y force CY | CYp = 0.020726 CYq = -0.872953 CYr = 0.678009 + x' mom. Cl'| Clp = -0.487842 Clq = -0.091053 Clr = 0.098084 + y mom. Cm | Cmp = -0.046431 Cmq = -73.149086 Cmr = 0.318043 + z' mom. Cn'| Cnp = -0.000704 Cnq = 0.416711 Cnr = -0.306077 + + Neutral point Xnp = 19.869659 + + Clb Cnr / Clr Cnb = 1.637978 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_001_04.txt b/regression/scripts/AVL/avl_files/results_case_001_04.txt new file mode 100644 index 0000000000..444aae74bc --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_001_04.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_001_04 + + 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 = 0.03675 Cltot = -0.00085 Cl'tot = -0.00056 + CYtot = -0.00702 Cmtot = -0.59493 + CZtot = -0.55319 Cntot = 0.00331 Cn'tot = 0.00337 + + CLtot = 0.55429 + CDtot = 0.01161 + CDvis = 0.00000 CDind = 0.0116078 + CLff = 0.55545 CDff = 0.0118050 | Trefftz + CYff = -0.00656 e = 0.8820 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.236655 CLb = 0.080840 + y force CY | CYa = -0.085628 CYb = -0.640867 + x' mom. Cl'| Cla = -0.002668 Clb = -0.100174 + y mom. Cm | Cma = -6.623202 Cmb = -0.278051 + z' mom. Cn'| Cna = 0.042218 Cnb = 0.157139 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.008382 CLq = 27.143610 CLr = -0.089486 + y force CY | CYp = 0.143427 CYq = -0.928945 CYr = 0.687301 + x' mom. Cl'| Clp = -0.482200 Clq = -0.063697 Clr = 0.151310 + y mom. Cm | Cmp = -0.031809 Cmq = -72.970505 Cmr = 0.311828 + z' mom. Cn'| Cnp = -0.051758 Cnq = 0.455203 Cnr = -0.320883 + + Neutral point Xnp = 19.807364 + + Clb Cnr / Clr Cnb = 1.351914 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_001_05.txt b/regression/scripts/AVL/avl_files/results_case_001_05.txt new file mode 100644 index 0000000000..a13fd76ee6 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_001_05.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_001_05 + + 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 = 0.07168 Cltot = -0.00119 Cl'tot = -0.00059 + CYtot = -0.01007 Cmtot = -0.82380 + CZtot = -0.76803 Cntot = 0.00478 Cn'tot = 0.00489 + + CLtot = 0.77104 + CDtot = 0.02245 + CDvis = 0.00000 CDind = 0.0224539 + CLff = 0.77410 CDff = 0.0229350 | Trefftz + CYff = -0.00919 e = 0.8817 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.179661 CLb = 0.079297 + y force CY | CYa = -0.088899 CYb = -0.651028 + x' mom. Cl'| Cla = 0.000737 Clb = -0.116840 + y mom. Cm | Cma = -6.484720 Cmb = -0.273608 + z' mom. Cn'| Cna = 0.044423 Cnb = 0.169915 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.005527 CLq = 27.191557 CLr = -0.087813 + y force CY | CYp = 0.225477 CYq = -0.964868 CYr = 0.686343 + x' mom. Cl'| Clp = -0.478153 Clq = -0.043287 Clr = 0.185711 + y mom. Cm | Cmp = -0.022457 Cmq = -72.740265 Cmr = 0.306849 + z' mom. Cn'| Cnp = -0.086587 Cnq = 0.479184 Cnr = -0.329818 + + Neutral point Xnp = 19.753939 + + Clb Cnr / Clr Cnb = 1.221227 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_001_06.txt b/regression/scripts/AVL/avl_files/results_case_001_06.txt new file mode 100644 index 0000000000..cbb1411e62 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_001_06.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_001_06 + + 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 = 0.14528 Cltot = -0.00167 Cl'tot = -0.00041 + CYtot = -0.01484 Cmtot = -1.15666 + CZtot = -1.08290 Cntot = 0.00710 Cn'tot = 0.00728 + + CLtot = 1.09168 + CDtot = 0.04498 + CDvis = 0.00000 CDind = 0.0449758 + CLff = 1.10021 CDff = 0.0463409 | Trefftz + CYff = -0.01311 e = 0.8815 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.061152 CLb = 0.077011 + y force CY | CYa = -0.092989 CYb = -0.664778 + x' mom. Cl'| Cla = 0.006255 Clb = -0.140068 + y mom. Cm | Cma = -6.218014 Cmb = -0.266320 + z' mom. Cn'| Cna = 0.046933 Cnb = 0.191179 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.001472 CLq = 27.254856 CLr = -0.085119 + y force CY | CYp = 0.347928 CYq = -1.016534 CYr = 0.674187 + x' mom. Cl'| Clp = -0.471839 Clq = -0.009663 Clr = 0.235687 + y mom. Cm | Cmp = -0.009136 Cmq = -72.228882 Cmr = 0.298189 + z' mom. Cn'| Cnp = -0.139806 Cnq = 0.512341 Cnr = -0.341616 + + Neutral point Xnp = 19.654480 + + Clb Cnr / Clr Cnb = 1.061936 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_002_01.txt b/regression/scripts/AVL/avl_files/results_case_002_01.txt new file mode 100644 index 0000000000..74f60dad66 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_002_01.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_002_01 + + 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 = 0.00575 Cltot = 0.00035 Cl'tot = 0.00039 + CYtot = 0.00260 Cmtot = 0.23363 + CZtot = 0.21462 Cntot = -0.00119 Cn'tot = -0.00118 + + CLtot = -0.21469 + CDtot = 0.00174 + CDvis = 0.00000 CDind = 0.0017417 + CLff = -0.21473 CDff = 0.0017686 | Trefftz + CYff = 0.00268 e = 0.8799 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.331619 CLb = 0.086425 + y force CY | CYa = -0.071122 CYb = -0.600373 + x' mom. Cl'| Cla = -0.012257 Clb = -0.035719 + y mom. Cm | Cma = -6.890664 Cmb = -0.291472 + z' mom. Cn'| Cna = 0.031680 Cnb = 0.122673 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.019265 CLq = 27.095776 CLr = -0.094532 + y force CY | CYp = -0.140222 CYq = -0.796732 CYr = 0.647097 + x' mom. Cl'| Clp = -0.496961 Clq = -0.121312 Clr = 0.024011 + y mom. Cm | Cmp = -0.066763 Cmq = -73.457108 Cmr = 0.324534 + z' mom. Cn'| Cnp = 0.064914 Cnq = 0.362314 Cnr = -0.284833 + + Neutral point Xnp = 19.918804 + + Clb Cnr / Clr Cnb = 3.454108 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_002_02.txt b/regression/scripts/AVL/avl_files/results_case_002_02.txt new file mode 100644 index 0000000000..6bd2db747d --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_002_02.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_002_02 + + 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 = -0.00000 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00003 Cmtot = -0.00659 + CZtot = -0.00651 Cntot = -0.00001 Cn'tot = -0.00001 + + CLtot = 0.00651 + CDtot = 0.00000 + CDvis = 0.00000 CDind = 0.0000017 + CLff = 0.00651 CDff = 0.0000016 | Trefftz + CYff = 0.00003 e = 0.8840 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.339318 CLb = 0.084887 + y force CY | CYa = -0.075779 CYb = -0.613245 + x' mom. Cl'| Cla = -0.009943 Clb = -0.055114 + y mom. Cm | Cma = -6.867140 Cmb = -0.288210 + z' mom. Cn'| Cna = 0.035113 Cnb = 0.131062 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.016012 CLq = 27.158924 CLr = -0.093323 + y force CY | CYp = -0.060085 CYq = -0.836532 CYr = 0.666066 + x' mom. Cl'| Clp = -0.494050 Clq = -0.107278 Clr = 0.061692 + y mom. Cm | Cmp = -0.056456 Cmq = -73.539139 Cmr = 0.321932 + z' mom. Cn'| Cnp = 0.032396 Cnq = 0.390603 Cnr = -0.296081 + + Neutral point Xnp = 19.897491 + + Clb Cnr / Clr Cnb = 2.018225 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_002_03.txt b/regression/scripts/AVL/avl_files/results_case_002_03.txt new file mode 100644 index 0000000000..80a2317e34 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_002_03.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_002_03 + + 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 = 0.00599 Cltot = -0.00034 Cl'tot = -0.00030 + CYtot = -0.00269 Cmtot = -0.24540 + CZtot = -0.22758 Cntot = 0.00126 Cn'tot = 0.00127 + + CLtot = 0.22766 + CDtot = 0.00195 + CDvis = 0.00000 CDind = 0.0019545 + CLff = 0.22775 CDff = 0.0019783 | Trefftz + CYff = -0.00261 e = 0.8848 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.328217 CLb = 0.083336 + y force CY | CYa = -0.080067 CYb = -0.625369 + x' mom. Cl'| Cla = -0.007274 Clb = -0.073877 + y mom. Cm | Cma = -6.810158 Cmb = -0.284596 + z' mom. Cn'| Cna = 0.038242 Cnb = 0.140783 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.012864 CLq = 27.218267 CLr = -0.091960 + y force CY | CYp = 0.021181 CYq = -0.875312 CYr = 0.679398 + x' mom. Cl'| Clp = -0.490716 Clq = -0.091305 Clr = 0.098542 + y mom. Cm | Cmp = -0.046356 Cmq = -73.531578 Cmr = 0.318618 + z' mom. Cn'| Cnp = -0.000918 Cnq = 0.417845 Cnr = -0.306789 + + Neutral point Xnp = 19.867405 + + Clb Cnr / Clr Cnb = 1.633729 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_002_04.txt b/regression/scripts/AVL/avl_files/results_case_002_04.txt new file mode 100644 index 0000000000..1fbcfc033e --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_002_04.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_002_04 + + 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 = 0.03693 Cltot = -0.00085 Cl'tot = -0.00056 + CYtot = -0.00703 Cmtot = -0.59844 + CZtot = -0.55673 Cntot = 0.00332 Cn'tot = 0.00338 + + CLtot = 0.55783 + CDtot = 0.01173 + CDvis = 0.00000 CDind = 0.0117344 + CLff = 0.55900 CDff = 0.0119367 | Trefftz + CYff = -0.00657 e = 0.8834 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.276549 CLb = 0.081001 + y force CY | CYa = -0.085761 CYb = -0.642123 + x' mom. Cl'| Cla = -0.002673 Clb = -0.100637 + y mom. Cm | Cma = -6.662610 Cmb = -0.278526 + z' mom. Cn'| Cna = 0.042283 Cnb = 0.157758 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.008350 CLq = 27.299517 CLr = -0.089657 + y force CY | CYp = 0.144327 CYq = -0.931469 CYr = 0.688695 + x' mom. Cl'| Clp = -0.485102 Clq = -0.063883 Clr = 0.152212 + y mom. Cm | Cmp = -0.031700 Cmq = -73.352303 Cmr = 0.312347 + z' mom. Cn'| Cnp = -0.052240 Cnq = 0.456454 Cnr = -0.321641 + + Neutral point Xnp = 19.805367 + + Clb Cnr / Clr Cnb = 1.348000 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_002_05.txt b/regression/scripts/AVL/avl_files/results_case_002_05.txt new file mode 100644 index 0000000000..5bd31e8026 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_002_05.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_002_05 + + 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 = 0.07204 Cltot = -0.00119 Cl'tot = -0.00060 + CYtot = -0.01009 Cmtot = -0.82867 + CZtot = -0.77296 Cntot = 0.00478 Cn'tot = 0.00489 + + CLtot = 0.77597 + CDtot = 0.02270 + CDvis = 0.00000 CDind = 0.0226993 + CLff = 0.77904 CDff = 0.0231908 | Trefftz + CYff = -0.00920 e = 0.8832 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.219150 CLb = 0.079450 + y force CY | CYa = -0.089038 CYb = -0.652316 + x' mom. Cl'| Cla = 0.000736 Clb = -0.117427 + y mom. Cm | Cma = -6.523556 Cmb = -0.274055 + z' mom. Cn'| Cna = 0.044492 Cnb = 0.170589 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.005488 CLq = 27.348124 CLr = -0.087974 + y force CY | CYp = 0.226673 CYq = -0.967498 CYr = 0.687713 + x' mom. Cl'| Clp = -0.481065 Clq = -0.043422 Clr = 0.186906 + y mom. Cm | Cmp = -0.022329 Cmq = -73.121040 Cmr = 0.307329 + z' mom. Cn'| Cnp = -0.087246 Cnq = 0.480509 Cnr = -0.330609 + + Neutral point Xnp = 19.752167 + + Clb Cnr / Clr Cnb = 1.217606 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_002_06.txt b/regression/scripts/AVL/avl_files/results_case_002_06.txt new file mode 100644 index 0000000000..ea1219b9f3 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_002_06.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_002_06 + + 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 = 0.14600 Cltot = -0.00167 Cl'tot = -0.00041 + CYtot = -0.01486 Cmtot = -1.16354 + CZtot = -1.08986 Cntot = 0.00711 Cn'tot = 0.00729 + + CLtot = 1.09865 + CDtot = 0.04547 + CDvis = 0.00000 CDind = 0.0454700 + CLff = 1.10723 CDff = 0.0468575 | Trefftz + CYff = -0.01313 e = 0.8830 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.099731 CLb = 0.077152 + y force CY | CYa = -0.093137 CYb = -0.666113 + x' mom. Cl'| Cla = 0.006262 Clb = -0.140833 + y mom. Cm | Cma = -6.255638 Cmb = -0.266723 + z' mom. Cn'| Cna = 0.047009 Cnb = 0.191953 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.001426 CLq = 27.412104 CLr = -0.085264 + y force CY | CYp = 0.349562 CYq = -1.019317 CYr = 0.675484 + x' mom. Cl'| Clp = -0.474754 Clq = -0.009712 Clr = 0.237319 + y mom. Cm | Cmp = -0.008984 Cmq = -72.607193 Cmr = 0.298608 + z' mom. Cn'| Cnp = -0.140732 Cnq = 0.513769 Cnr = -0.342461 + + Neutral point Xnp = 19.653124 + + Clb Cnr / Clr Cnb = 1.058732 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_003_01.txt b/regression/scripts/AVL/avl_files/results_case_003_01.txt new file mode 100644 index 0000000000..18c71923c1 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_003_01.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_003_01 + + 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 = 0.00581 Cltot = 0.00035 Cl'tot = 0.00039 + CYtot = 0.00260 Cmtot = 0.23645 + CZtot = 0.21745 Cntot = -0.00120 Cn'tot = -0.00119 + + CLtot = -0.21752 + CDtot = 0.00178 + CDvis = 0.00000 CDind = 0.0017833 + CLff = -0.21755 CDff = 0.0018092 | Trefftz + CYff = 0.00268 e = 0.8829 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.415158 CLb = 0.086801 + y force CY | CYa = -0.071330 CYb = -0.602674 + x' mom. Cl'| Cla = -0.012294 Clb = -0.035724 + y mom. Cm | Cma = -6.974115 Cmb = -0.292637 + z' mom. Cn'| Cna = 0.031772 Cnb = 0.123681 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.019252 CLq = 27.413368 CLr = -0.094940 + y force CY | CYp = -0.140446 CYq = -0.801067 CYr = 0.649770 + x' mom. Cl'| Clp = -0.502880 Clq = -0.121964 Clr = 0.023723 + y mom. Cm | Cmp = -0.066716 Cmq = -74.246956 Cmr = 0.325852 + z' mom. Cn'| Cnp = 0.065152 Cnq = 0.364285 Cnr = -0.286172 + + Neutral point Xnp = 19.913877 + + Clb Cnr / Clr Cnb = 3.484289 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_003_02.txt b/regression/scripts/AVL/avl_files/results_case_003_02.txt new file mode 100644 index 0000000000..da17f81ef0 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_003_02.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_003_02 + + 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 = -0.00000 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00003 Cmtot = -0.00666 + CZtot = -0.00660 Cntot = -0.00002 Cn'tot = -0.00002 + + CLtot = 0.00660 + CDtot = 0.00000 + CDvis = 0.00000 CDind = 0.0000018 + CLff = 0.00660 CDff = 0.0000017 | Trefftz + CYff = 0.00003 e = 0.8865 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.422476 CLb = 0.085250 + y force CY | CYa = -0.076005 CYb = -0.615625 + x' mom. Cl'| Cla = -0.009974 Clb = -0.055397 + y mom. Cm | Cma = -6.949617 Cmb = -0.289316 + z' mom. Cn'| Cna = 0.035218 Cnb = 0.132119 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.015983 CLq = 27.476328 CLr = -0.093715 + y force CY | CYp = -0.059747 CYq = -0.841112 CYr = 0.668840 + x' mom. Cl'| Clp = -0.499927 Clq = -0.107868 Clr = 0.062022 + y mom. Cm | Cmp = -0.056351 Cmq = -74.327347 Cmr = 0.323177 + z' mom. Cn'| Cnp = 0.032319 Cnq = 0.392751 Cnr = -0.297473 + + Neutral point Xnp = 19.892477 + + Clb Cnr / Clr Cnb = 2.011040 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_003_03.txt b/regression/scripts/AVL/avl_files/results_case_003_03.txt new file mode 100644 index 0000000000..cf8bcccc10 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_003_03.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_003_03 + + 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 = 0.00605 Cltot = -0.00034 Cl'tot = -0.00030 + CYtot = -0.00270 Cmtot = -0.24833 + CZtot = -0.23056 Cntot = 0.00126 Cn'tot = 0.00127 + + CLtot = 0.23063 + CDtot = 0.00200 + CDvis = 0.00000 CDind = 0.0020007 + CLff = 0.23074 CDff = 0.0020240 | Trefftz + CYff = -0.00262 e = 0.8877 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.410632 CLb = 0.083684 + y force CY | CYa = -0.080310 CYb = -0.627826 + x' mom. Cl'| Cla = -0.007298 Clb = -0.074434 + y mom. Cm | Cma = -6.891263 Cmb = -0.285642 + z' mom. Cn'| Cna = 0.038359 Cnb = 0.141910 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.012819 CLq = 27.535149 CLr = -0.092334 + y force CY | CYp = 0.022085 CYq = -0.880131 CYr = 0.682235 + x' mom. Cl'| Clp = -0.496535 Clq = -0.091821 Clr = 0.099483 + y mom. Cm | Cmp = -0.046198 Cmq = -74.317192 Cmr = 0.319786 + z' mom. Cn'| Cnp = -0.001316 Cnq = 0.420165 Cnr = -0.308242 + + Neutral point Xnp = 19.862392 + + Clb Cnr / Clr Cnb = 1.625183 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_003_04.txt b/regression/scripts/AVL/avl_files/results_case_003_04.txt new file mode 100644 index 0000000000..fefee46f38 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_003_04.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_003_04 + + 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 = 0.03729 Cltot = -0.00086 Cl'tot = -0.00056 + CYtot = -0.00706 Cmtot = -0.60554 + CZtot = -0.56398 Cntot = 0.00333 Cn'tot = 0.00339 + + CLtot = 0.56508 + CDtot = 0.01201 + CDvis = 0.00000 CDind = 0.0120084 + CLff = 0.56633 CDff = 0.0122117 | Trefftz + CYff = -0.00659 e = 0.8864 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.357182 CLb = 0.081324 + y force CY | CYa = -0.086028 CYb = -0.644689 + x' mom. Cl'| Cla = -0.002685 Clb = -0.101593 + y mom. Cm | Cma = -6.740913 Cmb = -0.279480 + z' mom. Cn'| Cna = 0.042415 Cnb = 0.159024 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.008283 CLq = 27.615005 CLr = -0.090000 + y force CY | CYp = 0.146086 CYq = -0.936636 CYr = 0.691549 + x' mom. Cl'| Clp = -0.490802 Clq = -0.064265 Clr = 0.154051 + y mom. Cm | Cmp = -0.031473 Cmq = -74.132210 Cmr = 0.313393 + z' mom. Cn'| Cnp = -0.053133 Cnq = 0.459020 Cnr = -0.323199 + + Neutral point Xnp = 19.800510 + + Clb Cnr / Clr Cnb = 1.340317 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_003_05.txt b/regression/scripts/AVL/avl_files/results_case_003_05.txt new file mode 100644 index 0000000000..cad1fe6a88 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_003_05.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_003_05 + + 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 = 0.07274 Cltot = -0.00119 Cl'tot = -0.00060 + CYtot = -0.01012 Cmtot = -0.83847 + CZtot = -0.78298 Cntot = 0.00480 Cn'tot = 0.00491 + + CLtot = 0.78601 + CDtot = 0.02323 + CDvis = 0.00000 CDind = 0.0232253 + CLff = 0.78926 CDff = 0.0237248 | Trefftz + CYff = -0.00923 e = 0.8861 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.298169 CLb = 0.079755 + y force CY | CYa = -0.089320 CYb = -0.654952 + x' mom. Cl'| Cla = 0.000734 Clb = -0.118640 + y mom. Cm | Cma = -6.599514 Cmb = -0.274946 + z' mom. Cn'| Cna = 0.044634 Cnb = 0.171971 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.005409 CLq = 27.662283 CLr = -0.088294 + y force CY | CYp = 0.229002 CYq = -0.972888 CYr = 0.690530 + x' mom. Cl'| Clp = -0.486667 Clq = -0.043701 Clr = 0.189330 + y mom. Cm | Cmp = -0.022063 Cmq = -73.895935 Cmr = 0.308290 + z' mom. Cn'| Cnp = -0.088480 Cnq = 0.483231 Cnr = -0.332245 + + Neutral point Xnp = 19.747507 + + Clb Cnr / Clr Cnb = 1.210640 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_003_06.txt b/regression/scripts/AVL/avl_files/results_case_003_06.txt new file mode 100644 index 0000000000..4b562fc3a4 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_003_06.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_003_06 + + 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 = 0.14742 Cltot = -0.00168 Cl'tot = -0.00042 + CYtot = -0.01491 Cmtot = -1.17721 + CZtot = -1.10392 Cntot = 0.00713 Cn'tot = 0.00732 + + CLtot = 1.11275 + CDtot = 0.04651 + CDvis = 0.00000 CDind = 0.0465112 + CLff = 1.12176 CDff = 0.0479361 | Trefftz + CYff = -0.01317 e = 0.8859 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.175738 CLb = 0.077427 + y force CY | CYa = -0.093437 CYb = -0.668847 + x' mom. Cl'| Cla = 0.006276 Clb = -0.142415 + y mom. Cm | Cma = -6.327388 Cmb = -0.267518 + z' mom. Cn'| Cna = 0.047162 Cnb = 0.193541 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.001331 CLq = 27.723684 CLr = -0.085546 + y force CY | CYp = 0.352736 CYq = -1.025031 CYr = 0.678170 + x' mom. Cl'| Clp = -0.480185 Clq = -0.009816 Clr = 0.240596 + y mom. Cm | Cmp = -0.008672 Cmq = -73.372856 Cmr = 0.299436 + z' mom. Cn'| Cnp = -0.142492 Cnq = 0.516711 Cnr = -0.344221 + + Neutral point Xnp = 19.648872 + + Clb Cnr / Clr Cnb = 1.052767 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_004_01.txt b/regression/scripts/AVL/avl_files/results_case_004_01.txt new file mode 100644 index 0000000000..3e55a5029e --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_004_01.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_004_01 + + 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 = 0.00601 Cltot = 0.00036 Cl'tot = 0.00040 + CYtot = 0.00263 Cmtot = 0.24735 + CZtot = 0.22846 Cntot = -0.00121 Cn'tot = -0.00120 + + CLtot = -0.22853 + CDtot = 0.00196 + CDvis = 0.00000 CDind = 0.0019632 + CLff = -0.22856 CDff = 0.0019721 | Trefftz + CYff = 0.00271 e = 0.8940 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.740010 CLb = 0.088173 + y force CY | CYa = -0.072057 CYb = -0.611228 + x' mom. Cl'| Cla = -0.012422 Clb = -0.035685 + y mom. Cm | Cma = -7.294997 Cmb = -0.296952 + z' mom. Cn'| Cna = 0.032093 Cnb = 0.127430 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.019177 CLq = 28.644444 CLr = -0.096429 + y force CY | CYp = -0.141168 CYq = -0.817218 CYr = 0.659728 + x' mom. Cl'| Clp = -0.525667 Clq = -0.124387 Clr = 0.022532 + y mom. Cm | Cmp = -0.066476 Cmq = -77.290611 Cmr = 0.330759 + z' mom. Cn'| Cnp = 0.065997 Cnq = 0.371645 Cnr = -0.291152 + + Neutral point Xnp = 19.893597 + + Clb Cnr / Clr Cnb = 3.618520 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_004_02.txt b/regression/scripts/AVL/avl_files/results_case_004_02.txt new file mode 100644 index 0000000000..35ec96c463 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_004_02.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_004_02 + + 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 = -0.00000 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00003 Cmtot = -0.00694 + CZtot = -0.00694 Cntot = -0.00002 Cn'tot = -0.00002 + + CLtot = 0.00694 + CDtot = 0.00000 + CDvis = 0.00000 CDind = 0.0000019 + CLff = 0.00694 CDff = 0.0000018 | Trefftz + CYff = 0.00003 e = 0.8958 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.747992 CLb = 0.086573 + y force CY | CYa = -0.076794 CYb = -0.624468 + x' mom. Cl'| Cla = -0.010085 Clb = -0.056447 + y mom. Cm | Cma = -7.268806 Cmb = -0.293414 + z' mom. Cn'| Cna = 0.035582 Cnb = 0.136048 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.015848 CLq = 28.712725 CLr = -0.095148 + y force CY | CYp = -0.058339 CYq = -0.858133 CYr = 0.679163 + x' mom. Cl'| Clp = -0.522698 Clq = -0.110060 Clr = 0.063252 + y mom. Cm | Cmp = -0.055894 Cmq = -77.370255 Cmr = 0.327812 + z' mom. Cn'| Cnp = 0.031972 Cnq = 0.400744 Cnr = -0.302641 + + Neutral point Xnp = 19.871738 + + Clb Cnr / Clr Cnb = 1.985172 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_004_03.txt b/regression/scripts/AVL/avl_files/results_case_004_03.txt new file mode 100644 index 0000000000..685ca1eb55 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_004_03.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_004_03 + + 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 = 0.00625 Cltot = -0.00035 Cl'tot = -0.00030 + CYtot = -0.00272 Cmtot = -0.25970 + CZtot = -0.24226 Cntot = 0.00127 Cn'tot = 0.00128 + + CLtot = 0.24233 + CDtot = 0.00220 + CDvis = 0.00000 CDind = 0.0022039 + CLff = 0.24244 CDff = 0.0022077 | Trefftz + CYff = -0.00265 e = 0.8985 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.735263 CLb = 0.084953 + y force CY | CYa = -0.081157 CYb = -0.636948 + x' mom. Cl'| Cla = -0.007385 Clb = -0.076556 + y mom. Cm | Cma = -7.207200 Cmb = -0.289519 + z' mom. Cn'| Cna = 0.038763 Cnb = 0.146093 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.012626 CLq = 28.775362 CLr = -0.093701 + y force CY | CYp = 0.025644 CYq = -0.898003 CYr = 0.692773 + x' mom. Cl'| Clp = -0.519219 Clq = -0.093738 Clr = 0.103116 + y mom. Cm | Cmp = -0.045543 Cmq = -77.355637 Cmr = 0.324134 + z' mom. Cn'| Cnp = -0.002872 Cnq = 0.428773 Cnr = -0.313634 + + Neutral point Xnp = 19.841623 + + Clb Cnr / Clr Cnb = 1.593853 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_004_04.txt b/regression/scripts/AVL/avl_files/results_case_004_04.txt new file mode 100644 index 0000000000..d00be85dcf --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_004_04.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_004_04 + + 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 = 0.03857 Cltot = -0.00087 Cl'tot = -0.00057 + CYtot = -0.00713 Cmtot = -0.63327 + CZtot = -0.59257 Cntot = 0.00336 Cn'tot = 0.00342 + + CLtot = 0.59368 + CDtot = 0.01323 + CDvis = 0.00000 CDind = 0.0132263 + CLff = 0.59505 CDff = 0.0133176 | Trefftz + CYff = -0.00666 e = 0.8973 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.677615 CLb = 0.082503 + y force CY | CYa = -0.086954 CYb = -0.654208 + x' mom. Cl'| Cla = -0.002730 Clb = -0.105285 + y mom. Cm | Cma = -7.049099 Cmb = -0.283016 + z' mom. Cn'| Cna = 0.042874 Cnb = 0.163728 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.008013 CLq = 28.858053 CLr = -0.091256 + y force CY | CYp = 0.152887 CYq = -0.955740 CYr = 0.702129 + x' mom. Cl'| Clp = -0.513232 Clq = -0.065691 Clr = 0.161241 + y mom. Cm | Cmp = -0.030560 Cmq = -77.157051 Cmr = 0.317287 + z' mom. Cn'| Cnp = -0.056536 Cnq = 0.468513 Cnr = -0.328988 + + Neutral point Xnp = 19.780478 + + Clb Cnr / Clr Cnb = 1.312044 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_004_05.txt b/regression/scripts/AVL/avl_files/results_case_004_05.txt new file mode 100644 index 0000000000..202c8af540 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_004_05.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_004_05 + + 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 = 0.07524 Cltot = -0.00121 Cl'tot = -0.00061 + CYtot = -0.01022 Cmtot = -0.87683 + CZtot = -0.82268 Cntot = 0.00485 Cn'tot = 0.00496 + + CLtot = 0.82572 + CDtot = 0.02558 + CDvis = 0.00000 CDind = 0.0255810 + CLff = 0.82927 CDff = 0.0258724 | Trefftz + CYff = -0.00933 e = 0.8970 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.613929 CLb = 0.080868 + y force CY | CYa = -0.090293 CYb = -0.664721 + x' mom. Cl'| Cla = 0.000722 Clb = -0.123345 + y mom. Cm | Cma = -6.900647 Cmb = -0.278249 + z' mom. Cn'| Cna = 0.045124 Cnb = 0.177112 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.005093 CLq = 28.905281 CLr = -0.089465 + y force CY | CYp = 0.237958 CYq = -0.992787 CYr = 0.700949 + x' mom. Cl'| Clp = -0.508847 Clq = -0.044750 Clr = 0.198849 + y mom. Cm | Cmp = -0.021004 Cmq = -76.907120 Cmr = 0.311867 + z' mom. Cn'| Cnp = -0.093142 Cnq = 0.493281 Cnr = -0.338335 + + Neutral point Xnp = 19.728468 + + Clb Cnr / Clr Cnb = 1.184937 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_004_06.txt b/regression/scripts/AVL/avl_files/results_case_004_06.txt new file mode 100644 index 0000000000..dc25c288b8 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_004_06.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_004_06 + + 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 = 0.15250 Cltot = -0.00170 Cl'tot = -0.00042 + CYtot = -0.01507 Cmtot = -1.23100 + CZtot = -1.15989 Cntot = 0.00721 Cn'tot = 0.00739 + + CLtot = 1.16875 + CDtot = 0.05123 + CDvis = 0.00000 CDind = 0.0512300 + CLff = 1.17862 CDff = 0.0522739 | Trefftz + CYff = -0.01330 e = 0.8968 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 6.481776 CLb = 0.078433 + y force CY | CYa = -0.094472 CYb = -0.678968 + x' mom. Cl'| Cla = 0.006319 Clb = -0.148575 + y mom. Cm | Cma = -6.615207 Cmb = -0.270465 + z' mom. Cn'| Cna = 0.047691 Cnb = 0.199468 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.000957 CLq = 28.963709 CLr = -0.086579 + y force CY | CYp = 0.364892 CYq = -1.046074 CYr = 0.688067 + x' mom. Cl'| Clp = -0.501878 Clq = -0.010228 Clr = 0.253529 + y mom. Cm | Cmp = -0.007438 Cmq = -76.356651 Cmr = 0.302522 + z' mom. Cn'| Cnp = -0.149088 Cnq = 0.527547 Cnr = -0.350811 + + Neutral point Xnp = 19.632059 + + Clb Cnr / Clr Cnb = 1.030668 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_005_01.txt b/regression/scripts/AVL/avl_files/results_case_005_01.txt new file mode 100644 index 0000000000..642fe3765f --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_005_01.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_005_01 + + 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 = 0.00642 Cltot = 0.00036 Cl'tot = 0.00040 + CYtot = 0.00267 Cmtot = 0.26894 + CZtot = 0.25087 Cntot = -0.00123 Cn'tot = -0.00122 + + CLtot = -0.25094 + CDtot = 0.00234 + CDvis = 0.00000 CDind = 0.0023395 + CLff = -0.25097 CDff = 0.0023253 | Trefftz + CYff = 0.00276 e = 0.9141 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 7.401773 CLb = 0.090505 + y force CY | CYa = -0.073124 CYb = -0.626576 + x' mom. Cl'| Cla = -0.012610 Clb = -0.035331 + y mom. Cm | Cma = -7.931043 Cmb = -0.304604 + z' mom. Cn'| Cna = 0.032565 Cnb = 0.134161 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.018925 CLq = 31.125977 CLr = -0.098989 + y force CY | CYp = -0.142005 CYq = -0.846187 CYr = 0.677688 + x' mom. Cl'| Clp = -0.570777 Clq = -0.128687 Clr = 0.019788 + y mom. Cm | Cmp = -0.065750 Cmq = -83.285912 Cmr = 0.339590 + z' mom. Cn'| Cnp = 0.067500 Cnq = 0.384931 Cnr = -0.300107 + + Neutral point Xnp = 19.847706 + + Clb Cnr / Clr Cnb = 3.994046 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_005_02.txt b/regression/scripts/AVL/avl_files/results_case_005_02.txt new file mode 100644 index 0000000000..0f2b616fb8 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_005_02.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_005_02 + + 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 = -0.00000 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00004 Cmtot = -0.00749 + CZtot = -0.00765 Cntot = -0.00002 Cn'tot = -0.00002 + + CLtot = 0.00765 + CDtot = 0.00000 + CDvis = 0.00000 CDind = 0.0000023 + CLff = 0.00765 CDff = 0.0000022 | Trefftz + CYff = 0.00004 e = 0.9134 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 7.410267 CLb = 0.088817 + y force CY | CYa = -0.077943 CYb = -0.640306 + x' mom. Cl'| Cla = -0.010248 Clb = -0.058313 + y mom. Cm | Cma = -7.901005 Cmb = -0.300666 + z' mom. Cn'| Cna = 0.036110 Cnb = 0.143070 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.015492 CLq = 31.202406 CLr = -0.097603 + y force CY | CYp = -0.055094 CYq = -0.888472 CYr = 0.697736 + x' mom. Cl'| Clp = -0.567848 Clq = -0.113954 Clr = 0.065464 + y mom. Cm | Cmp = -0.054772 Cmq = -83.360550 Cmr = 0.336140 + z' mom. Cn'| Cnp = 0.031047 Cnq = 0.415054 Cnr = -0.311896 + + Neutral point Xnp = 19.825336 + + Clb Cnr / Clr Cnb = 1.941881 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_005_03.txt b/regression/scripts/AVL/avl_files/results_case_005_03.txt new file mode 100644 index 0000000000..ceb40d0f07 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_005_03.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_005_03 + + 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 = 0.00666 Cltot = -0.00035 Cl'tot = -0.00031 + CYtot = -0.00276 Cmtot = -0.28220 + CZtot = -0.26605 Cntot = 0.00129 Cn'tot = 0.00130 + + CLtot = 0.26612 + CDtot = 0.00263 + CDvis = 0.00000 CDind = 0.0026275 + CLff = 0.26626 CDff = 0.0026060 | Trefftz + CYff = -0.00268 e = 0.9181 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 7.394846 CLb = 0.087098 + y force CY | CYa = -0.082382 CYb = -0.653255 + x' mom. Cl'| Cla = -0.007517 Clb = -0.080617 + y mom. Cm | Cma = -7.832476 Cmb = -0.296362 + z' mom. Cn'| Cna = 0.039344 Cnb = 0.153561 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.012172 CLq = 31.269762 CLr = -0.096036 + y force CY | CYp = 0.033004 CYq = -0.929674 CYr = 0.711672 + x' mom. Cl'| Clp = -0.564267 Clq = -0.097156 Clr = 0.110259 + y mom. Cm | Cmp = -0.044061 Cmq = -83.333641 Cmr = 0.331933 + z' mom. Cn'| Cnp = -0.006245 Cnq = 0.444076 Cnr = -0.323265 + + Neutral point Xnp = 19.795507 + + Clb Cnr / Clr Cnb = 1.539191 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_005_04.txt b/regression/scripts/AVL/avl_files/results_case_005_04.txt new file mode 100644 index 0000000000..a08114e129 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_005_04.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_005_04 + + 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 = 0.04110 Cltot = -0.00088 Cl'tot = -0.00058 + CYtot = -0.00723 Cmtot = -0.68812 + CZtot = -0.65066 Cntot = 0.00341 Cn'tot = 0.00347 + + CLtot = 0.65177 + CDtot = 0.01576 + CDvis = 0.00000 CDind = 0.0157612 + CLff = 0.65347 CDff = 0.0157156 | Trefftz + CYff = -0.00676 e = 0.9170 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 7.327221 CLb = 0.084483 + y force CY | CYa = -0.088281 CYb = -0.671182 + x' mom. Cl'| Cla = -0.002806 Clb = -0.112567 + y mom. Cm | Cma = -7.658287 Cmb = -0.289231 + z' mom. Cn'| Cna = 0.043526 Cnb = 0.172149 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.007426 CLq = 31.353045 CLr = -0.093383 + y force CY | CYp = 0.166435 CYq = -0.989339 CYr = 0.720977 + x' mom. Cl'| Clp = -0.557865 Clq = -0.068268 Clr = 0.175700 + y mom. Cm | Cmp = -0.028610 Cmq = -83.102928 Cmr = 0.324248 + z' mom. Cn'| Cnp = -0.063636 Cnq = 0.485237 Cnr = -0.339318 + + Neutral point Xnp = 19.736229 + + Clb Cnr / Clr Cnb = 1.262823 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_005_05.txt b/regression/scripts/AVL/avl_files/results_case_005_05.txt new file mode 100644 index 0000000000..0d1885338c --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_005_05.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_005_05 + + 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 = 0.08020 Cltot = -0.00123 Cl'tot = -0.00062 + CYtot = -0.01038 Cmtot = -0.95271 + CZtot = -0.90327 Cntot = 0.00492 Cn'tot = 0.00503 + + CLtot = 0.90631 + CDtot = 0.03048 + CDvis = 0.00000 CDind = 0.0304774 + CLff = 0.91069 CDff = 0.0305291 | Trefftz + CYff = -0.00946 e = 0.9168 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 7.253020 CLb = 0.082727 + y force CY | CYa = -0.091680 CYb = -0.682115 + x' mom. Cl'| Cla = 0.000689 Clb = -0.132711 + y mom. Cm | Cma = -7.495391 Cmb = -0.284035 + z' mom. Cn'| Cna = 0.045818 Cnb = 0.186354 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.004429 CLq = 31.396343 CLr = -0.091437 + y force CY | CYp = 0.255615 CYq = -1.027619 CYr = 0.719404 + x' mom. Cl'| Clp = -0.553037 Clq = -0.046686 Clr = 0.218111 + y mom. Cm | Cmp = -0.018792 Cmq = -82.822502 Cmr = 0.318244 + z' mom. Cn'| Cnp = -0.102770 Cnq = 0.510901 Cnr = -0.349215 + + Neutral point Xnp = 19.686398 + + Clb Cnr / Clr Cnb = 1.140210 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_005_06.txt b/regression/scripts/AVL/avl_files/results_case_005_06.txt new file mode 100644 index 0000000000..87117e43ef --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_005_06.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_005_06 + + 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 = 0.16257 Cltot = -0.00173 Cl'tot = -0.00044 + CYtot = -0.01529 Cmtot = -1.33734 + CZtot = -1.27339 Cntot = 0.00732 Cn'tot = 0.00751 + + CLtot = 1.28228 + CDtot = 0.06102 + CDvis = 0.00000 CDind = 0.0610188 + CLff = 1.29433 CDff = 0.0616797 | Trefftz + CYff = -0.01350 e = 0.9166 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 7.099554 CLb = 0.080095 + y force CY | CYa = -0.095937 CYb = -0.696951 + x' mom. Cl'| Cla = 0.006360 Clb = -0.160948 + y mom. Cm | Cma = -7.182875 Cmb = -0.275594 + z' mom. Cn'| Cna = 0.048437 Cnb = 0.210207 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.000197 CLq = 31.442436 CLr = -0.088296 + y force CY | CYp = 0.388635 CYq = -1.082677 CYr = 0.705398 + x' mom. Cl'| Clp = -0.545165 Clq = -0.011089 Clr = 0.279849 + y mom. Cm | Cmp = -0.004910 Cmq = -82.212814 Cmr = 0.307993 + z' mom. Cn'| Cnp = -0.162586 Cnq = 0.546420 Cnr = -0.362628 + + Neutral point Xnp = 19.594582 + + Clb Cnr / Clr Cnb = 0.992148 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_006_01.txt b/regression/scripts/AVL/avl_files/results_case_006_01.txt new file mode 100644 index 0000000000..f57425f9eb --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_006_01.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_006_01 + + 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 = 0.00722 Cltot = 0.00037 Cl'tot = 0.00041 + CYtot = 0.00270 Cmtot = 0.31582 + CZtot = 0.30211 Cntot = -0.00124 Cn'tot = -0.00123 + + CLtot = -0.30217 + CDtot = 0.00333 + CDvis = 0.00000 CDind = 0.0033275 + CLff = -0.30220 CDff = 0.0032459 | Trefftz + CYff = 0.00278 e = 0.9495 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 8.914166 CLb = 0.093869 + y force CY | CYa = -0.073677 CYb = -0.652952 + x' mom. Cl'| Cla = -0.012702 Clb = -0.033382 + y mom. Cm | Cma = -9.312452 Cmb = -0.316752 + z' mom. Cn'| Cna = 0.032816 Cnb = 0.145658 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.017986 CLq = 36.718418 CLr = -0.102841 + y force CY | CYp = -0.141329 CYq = -0.893768 CYr = 0.709066 + x' mom. Cl'| Clp = -0.667750 Clq = -0.135425 Clr = 0.012173 + y mom. Cm | Cmp = -0.063145 Cmq = -96.100090 Cmr = 0.354385 + z' mom. Cn'| Cnp = 0.069875 Cnq = 0.407217 Cnr = -0.315658 + + Neutral point Xnp = 19.734098 + + Clb Cnr / Clr Cnb = 5.942683 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_006_02.txt b/regression/scripts/AVL/avl_files/results_case_006_02.txt new file mode 100644 index 0000000000..da9b3ab382 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_006_02.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_006_02 + + 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 = -0.00000 Cltot = 0.00000 Cl'tot = 0.00000 + CYtot = 0.00004 Cmtot = -0.00868 + CZtot = -0.00926 Cntot = -0.00002 Cn'tot = -0.00002 + + CLtot = 0.00926 + CDtot = 0.00000 + CDvis = 0.00000 CDind = 0.0000033 + CLff = 0.00926 CDff = 0.0000031 | Trefftz + CYff = 0.00004 e = 0.9460 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 8.924268 CLb = 0.092030 + y force CY | CYa = -0.078490 CYb = -0.667377 + x' mom. Cl'| Cla = -0.010343 Clb = -0.061415 + y mom. Cm | Cma = -9.272793 Cmb = -0.312088 + z' mom. Cn'| Cna = 0.036357 Cnb = 0.154926 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.014395 CLq = 36.814823 CLr = -0.101270 + y force CY | CYp = -0.046380 CYq = -0.937353 CYr = 0.729964 + x' mom. Cl'| Clp = -0.664814 Clq = -0.120068 Clr = 0.069272 + y mom. Cm | Cmp = -0.051475 Cmq = -96.156944 Cmr = 0.350026 + z' mom. Cn'| Cnp = 0.028161 Cnq = 0.438460 Cnr = -0.327770 + + Neutral point Xnp = 19.710270 + + Clb Cnr / Clr Cnb = 1.875688 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_006_03.txt b/regression/scripts/AVL/avl_files/results_case_006_03.txt new file mode 100644 index 0000000000..460ae32e1d --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_006_03.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_006_03 + + 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 = 0.00745 Cltot = -0.00035 Cl'tot = -0.00031 + CYtot = -0.00277 Cmtot = -0.33101 + CZtot = -0.32042 Cntot = 0.00129 Cn'tot = 0.00131 + + CLtot = 0.32048 + CDtot = 0.00374 + CDvis = 0.00000 CDind = 0.0037410 + CLff = 0.32071 CDff = 0.0036441 | Trefftz + CYff = -0.00270 e = 0.9525 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 8.902308 CLb = 0.090141 + y force CY | CYa = -0.082920 CYb = -0.680990 + x' mom. Cl'| Cla = -0.007617 Clb = -0.088734 + y mom. Cm | Cma = -9.187959 Cmb = -0.307043 + z' mom. Cn'| Cna = 0.039587 Cnb = 0.166128 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.010928 CLq = 36.892666 CLr = -0.099490 + y force CY | CYp = 0.049795 CYq = -0.979795 CYr = 0.744187 + x' mom. Cl'| Clp = -0.660878 Clq = -0.102567 Clr = 0.125445 + y mom. Cm | Cmp = -0.040138 Cmq = -96.096657 Cmr = 0.344864 + z' mom. Cn'| Cnp = -0.014430 Cnq = 0.468555 Cnr = -0.339674 + + Neutral point Xnp = 19.680769 + + Clb Cnr / Clr Cnb = 1.446293 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_006_04.txt b/regression/scripts/AVL/avl_files/results_case_006_04.txt new file mode 100644 index 0000000000..87161b5059 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_006_04.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_006_04 + + 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 = 0.04603 Cltot = -0.00089 Cl'tot = -0.00059 + CYtot = -0.00727 Cmtot = -0.80701 + CZtot = -0.78347 Cntot = 0.00343 Cn'tot = 0.00349 + + CLtot = 0.78450 + CDtot = 0.02243 + CDvis = 0.00000 CDind = 0.0224258 + CLff = 0.78704 CDff = 0.0219651 | Trefftz + CYff = -0.00680 e = 0.9517 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 8.809783 CLb = 0.087236 + y force CY | CYa = -0.088802 CYb = -0.699847 + x' mom. Cl'| Cla = -0.002913 Clb = -0.128081 + y mom. Cm | Cma = -8.976963 Cmb = -0.298777 + z' mom. Cn'| Cna = 0.043764 Cnb = 0.186432 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.005986 CLq = 36.973843 CLr = -0.096465 + y force CY | CYp = 0.195332 CYq = -1.041203 CYr = 0.752866 + x' mom. Cl'| Clp = -0.653304 Clq = -0.072490 Clr = 0.207785 + y mom. Cm | Cmp = -0.023877 Cmq = -95.786758 Cmr = 0.335671 + z' mom. Cn'| Cnp = -0.079876 Cnq = 0.511227 Cnr = -0.356909 + + Neutral point Xnp = 19.625244 + + Clb Cnr / Clr Cnb = 1.180068 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_006_05.txt b/regression/scripts/AVL/avl_files/results_case_006_05.txt new file mode 100644 index 0000000000..1f53f9a23f --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_006_05.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_006_05 + + 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 = 0.08985 Cltot = -0.00124 Cl'tot = -0.00063 + CYtot = -0.01043 Cmtot = -1.11707 + CZtot = -1.08750 Cntot = 0.00495 Cn'tot = 0.00506 + + CLtot = 1.09035 + CDtot = 0.04335 + CDvis = 0.00000 CDind = 0.0433534 + CLff = 1.09680 CDff = 0.0426653 | Trefftz + CYff = -0.00952 e = 0.9515 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 8.709157 CLb = 0.085265 + y force CY | CYa = -0.092186 CYb = -0.711356 + x' mom. Cl'| Cla = 0.000578 Clb = -0.153039 + y mom. Cm | Cma = -8.781471 Cmb = -0.292810 + z' mom. Cn'| Cna = 0.046052 Cnb = 0.202207 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = 0.002879 CLq = 37.003838 CLr = -0.094241 + y force CY | CYp = 0.292516 CYq = -1.080567 CYr = 0.750173 + x' mom. Cl'| Clp = -0.647283 Clq = -0.050030 Clr = 0.261298 + y mom. Cm | Cmp = -0.013609 Cmq = -95.434212 Cmr = 0.328619 + z' mom. Cn'| Cnp = -0.124474 Cnq = 0.537826 Cnr = -0.367835 + + Neutral point Xnp = 19.580044 + + Clb Cnr / Clr Cnb = 1.065427 ( > 1 if spirally stable ) diff --git a/regression/scripts/AVL/avl_files/results_case_006_06.txt b/regression/scripts/AVL/avl_files/results_case_006_06.txt new file mode 100644 index 0000000000..d93aafa503 --- /dev/null +++ b/regression/scripts/AVL/avl_files/results_case_006_06.txt @@ -0,0 +1,53 @@ + --------------------------------------------------------------- + Vortex Lattice Output -- Total Forces + + Configuration: cruise + # Surfaces = 7 + # Strips = 162 + # Vortices =3240 + + Sref = 124.86 Cref = 4.2350 Bref = 34.320 + Xref = 15.310 Yref = 0.0000 Zref =-0.48024 + + Standard axis orientation, X fwd, Z down + + Run case: case_006_06 + + 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 = 0.18218 Cltot = -0.00176 Cl'tot = -0.00045 + CYtot = -0.01538 Cmtot = -1.56752 + CZtot = -1.53288 Cntot = 0.00735 Cn'tot = 0.00754 + + CLtot = 1.54122 + CDtot = 0.08677 + CDvis = 0.00000 CDind = 0.0867686 + CLff = 1.55883 CDff = 0.0861927 | Trefftz + CYff = -0.01359 e = 0.9514 | Plane + + + --------------------------------------------------------------- + + Stability-axis derivatives... + + alpha beta + ---------------- ---------------- + z' force CL | CLa = 8.501976 CLb = 0.082280 + y force CY | CYa = -0.096415 CYb = -0.726991 + x' mom. Cl'| Cla = 0.006242 Clb = -0.188263 + y mom. Cm | Cma = -8.408373 Cmb = -0.283193 + z' mom. Cn'| Cna = 0.048667 Cnb = 0.229035 + + roll rate p' pitch rate q' yaw rate r' + ---------------- ---------------- ---------------- + z' force CL | CLp = -0.001482 CLq = 37.012295 CLr = -0.090639 + y force CY | CYp = 0.437348 CYq = -1.137130 CYr = 0.733448 + x' mom. Cl'| Clp = -0.637035 Clq = -0.012999 Clr = 0.339354 + y mom. Cm | Cmp = 0.000810 Cmq = -94.687561 Cmr = 0.316741 + z' mom. Cn'| Cnp = -0.192667 Cnq = 0.574628 Cnr = -0.383119 + + Neutral point Xnp = 19.498253 + + Clb Cnr / Clr Cnb = 0.927991 ( > 1 if spirally stable ) diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/__init__.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/__init__.py new file mode 100644 index 0000000000..9ca53038d6 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/__init__.py @@ -0,0 +1,16 @@ +## @defgroup Methods-Weights-Correlations-General_Aviation Generational +# Provides structural and component weight correlations for general aviation aircraft +# @ingroup Methods-Weights-Correlations + +from empty import empty +from landing_gear import landing_gear +from payload import payload +from systems import systems +from tail_horizontal import tail_horizontal +from tail_vertical import tail_vertical +from fuselage import fuselage +from wing_main import wing_main + + + + diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py new file mode 100644 index 0000000000..ed8ed9590b --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py @@ -0,0 +1,376 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# empty.py +# +# Created: Feb 2018, M. Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- +import SUAVE +from SUAVE.Core import Units, Data +from fuselage import fuselage +from landing_gear import landing_gear +from payload import payload +from systems import systems +from tail_horizontal import tail_horizontal +from tail_vertical import tail_vertical +from wing_main import wing_main +from SUAVE.Methods.Weights.Correlations import Propulsion as Propulsion +import warnings + +# ---------------------------------------------------------------------- +# Empty +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-General_Aviation +def empty(vehicle): + """ output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical) + Computes the empty weight breakdown of a General Aviation type aircraft + + Inputs: + engine - a data dictionary with the fields: + thrust_sls - sea level static thrust of a single engine [Newtons] + + vehicle - a data dictionary with the fields: + reference_area [meters**2] + envelope - a data dictionary with the fields: + ultimate_load - ultimate load of the aircraft [dimensionless] + limit_load - limit load factor at zero fuel weight of the aircraft [dimensionless] + + mass_properties - a data dictionary with the fields: + max_takeoff - max takeoff weight of the vehicle [kilograms] + max_zero_fuel - maximum zero fuel weight of the aircraft [kilograms] + cargo - cargo weight [kilograms] + + passengers - number of passengers on the aircraft [dimensionless] + + design_dynamic_pressure - dynamic pressure at cruise conditions [Pascal] + design_mach_number - mach number at cruise conditions [dimensionless] + + propulsors - a data dictionary with the fields: + keys - identifier for the type of propulsor; different types have different fields + turbofan + thrust_sls - sealevel standard thrust [Newtons] + internal_combustion + rated_power - maximum rated power of the internal combustion engine [Watts] + + number_engines - integer indicating the number of engines on the aircraft + + wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms] + num_seats - number of seats installed on the aircraft [dimensionless] + ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless] + ac - determines type of instruments, electronics, and operating items based on types: + "short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless] + w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters] + + fuel - a data dictionary with the fields: + mass_properties - a data dictionary with the fields: + mass -mass of fuel [kilograms] + density - gravimetric density of fuel [kilograms/meter**3] + number_of_tanks - number of external fuel tanks [dimensionless] + internal_volume - internal fuel volume contained in the wing [meters**3] + wings - a data dictionary with the fields: + wing - a data dictionary with the fields: + span - span of the wing [meters] + taper - taper ratio of the wing [dimensionless] + thickness_to_chord - thickness-to-chord ratio of the wing [dimensionless] + chords - a data dictionary with the fields: + mean_aerodynamic - mean aerodynamic chord of the wing [meters] + root - root chord of the wing [meters] + + + sweeps - a data dictionary with the fields: + quarter_chord - quarter chord sweep angle of the wing [radians] + mac - mean aerodynamic chord of the wing [meters] + r_c - wing root chord [meters] + origin - location of the leading edge of the wing relative to the front of the fuselage [meters,meters,meters] + aerodynamic_center - location of the aerodynamic center of the horizontal_stabilizer relative to the leading edge of the wing [meters,meters,meters] + + + + + horizontal_stabilizer - a data dictionary with the fields: + areas - a data dictionary with the fields: + reference - reference area of the horizontal stabilizer [meters**2] + exposed - exposed area for the horizontal tail [meters**2] + taper - taper ratio of the horizontal stabilizer [dimensionless] + span - span of the horizontal tail [meters] + sweeps - a data dictionary with the fields: + quarter_chord - quarter chord sweep angle of the horizontal stabilizer [radians] + chords - a data dictionary with the fields: + mean_aerodynamic - mean aerodynamic chord of the horizontal stabilizer [meters] + root - root chord of the horizontal stabilizer + thickness_to_chord - thickness-to-chord ratio of the horizontal tail [dimensionless] + mac - mean aerodynamic chord of the horizontal tail [meters] + origin - location of the leading of the horizontal tail relative to the front of the fuselage [meters,meters,meters] + aerodynamic_center - location of the aerodynamic center of the horizontal_stabilizer relative to the leading edge of the horizontal stabilizer [meters,meters,meters] + + vertical - a data dictionary with the fields: + areas - a data dictionary with the fields: + reference - reference area of the vertical stabilizer [meters**2] + span - span of the vertical tail [meters] + taper - taper ratio of the horizontal stabilizer [dimensionless] + t_c - thickness-to-chord ratio of the vertical tail [dimensionless] + sweeps - a data dictionary with the fields: + quarter_chord - quarter chord sweep angle of the vertical stabilizer [radians] + t_tail - flag to determine if aircraft has a t-tail, "yes" [dimensionless] + + + + fuselages - a data dictionary with the fields: + fuselage - a data dictionary with the fields: + areas - a data dictionary with the fields: + wetted - wetted area of the fuselage [meters**2] + differential_pressure - Maximum fuselage pressure differential [Pascal] + width - width of the fuselage [meters] + heights - a data dictionary with the fields: + maximum - height of the fuselage [meters] + lengths- a data dictionary with the fields: + structure - structural length of the fuselage [meters] + mass_properties - a data dictionary with the fields: + volume - total volume of the fuselage [meters**3] + internal_volume - internal volume of the fuselage [meters**3] + number_coach_sets - number of seats on the aircraft [dimensionless] + landing_gear - a data dictionary with the fields: + main - a data dictionary with the fields: + strut_length - strut length of the main gear [meters] + nose - a data dictionary with the fields: + strut_length - strut length of the nose gear [meters] + avionics - a data dictionary, used to determine if avionics weight is calculated, don't include if vehicle has none + air_conditioner - a data dictionary, used to determine if air conditioner weight is calculated, don't include if vehicle has none + + + Outputs: + output - a data dictionary with fields: + wing - wing weight [kilograms] + fuselage - fuselage weight [kilograms] + propulsion - propulsion [kilograms] + landing_gear_main - main gear weight [kilograms] + landing_gear_nose - nose gear weight [kilograms] + horizonal_tail - horizontal stabilizer weight [kilograms] + vertical_tail - vertical stabilizer weight [kilograms] + systems - total systems weight [kilograms] + systems_breakdown - a data dictionary with fields: + control_systems - control systems weight [kilograms] + hydraulics - hydraulics weight [kilograms] + avionics - avionics weight [kilograms] + electric - electrical systems weight [kilograms] + air_conditioner - air conditioner weight [kilograms] + furnish - furnishing weight [kilograms] + fuel_system - fuel system weight [ kilograms] + Wing, empannage, fuselage, propulsion and individual systems masses updated with their calculated values + Assumptions: + calculated aircraft weight from correlations created per component of historical aircraft + + """ + + # Unpack inputs + S_gross_w = vehicle.reference_area + fuel = vehicle.fuel + Nult = vehicle.envelope.ultimate_load + Nlim = vehicle.envelope.limit_load + TOW = vehicle.mass_properties.max_takeoff + wt_zf = vehicle.mass_properties.max_zero_fuel + num_pax = vehicle.passengers + wt_cargo = vehicle.mass_properties.cargo + + q_c = vehicle.design_dynamic_pressure + mach_number = vehicle.design_mach_number + + propulsor_name = vehicle.propulsors.keys()[0] #obtain the key for the propulsor for assignment purposes + propulsors = vehicle.propulsors[propulsor_name] + num_eng = propulsors.number_of_engines + + if propulsor_name == 'turbofan': + thrust_sls = propulsors.sealevel_static_thrust + wt_engine_jet = Propulsion.engine_jet(thrust_sls) + wt_propulsion = Propulsion.integrated_propulsion(wt_engine_jet,num_eng) + propulsors.mass_properties.mass = wt_propulsion + + elif propulsor_name == 'internal_combustion': + rated_power = propulsors.rated_power/num_eng + wt_engine_piston = Propulsion.engine_piston(rated_power) + wt_propulsion = Propulsion.integrated_propulsion_general_aviation(wt_engine_piston,num_eng) + propulsors.mass_properties.mass = wt_propulsion + + else: #propulsor used is not an IC Engine or Turbofan; assume mass_properties defined outside model + wt_propulsion = propulsors.mass_properties.mass + if wt_propulsion==0: + warnings.warn("Propulsion mass= 0 ;e there is no Engine Weight being added to the Configuration", stacklevel=1) + #find fuel volume + if not vehicle.has_key('fuel'): + warnings.warn("fuel mass= 0 ; fuel system volume is calculated incorrectly ", stacklevel=1) + N_tank = 0 + V_fuel = 0. + V_fuel_int = 0. + + else: + m_fuel = fuel.mass_properties.mass + landing_weight = TOW-m_fuel #just assume this for now + N_tank = fuel.number_of_tanks + V_fuel_int = fuel.internal_volume #fuel in internal (as opposed to external tanks) + V_fuel = m_fuel/fuel.density #total fuel + fuel.mass_properties.volume = V_fuel + + #main wing + if not vehicle.wings.has_key('main_wing'): + wt_wing = 0.0 + wing_c_r = 0.0 + warnings.warn("There is no Wing Weight being added to the Configuration", stacklevel=1) + + else: + b = vehicle.wings['main_wing'].spans.projected + AR_w = (b**2.)/S_gross_w + taper_w = vehicle.wings['main_wing'].taper + t_c_w = vehicle.wings['main_wing'].thickness_to_chord + sweep_w = vehicle.wings['main_wing'].sweeps.quarter_chord + mac_w = vehicle.wings['main_wing'].chords.mean_aerodynamic + wing_c_r = vehicle.wings['main_wing'].chords.root + #now run weight script for the wing + wt_wing = wing_main(S_gross_w, m_fuel, AR_w, sweep_w, q_c, taper_w, t_c_w,Nult,TOW) + vehicle.wings['main_wing'].mass_properties.mass = wt_wing + + if not vehicle.wings.has_key('horizontal_stabilizer'): + wt_tail_horizontal = 0.0 + S_h = 0.0 + warnings.warn("There is no Horizontal Tail Weight being added to the Configuration", stacklevel=1) + + else: + S_h = vehicle.wings['horizontal_stabilizer'].areas.reference + b_h = vehicle.wings['horizontal_stabilizer'].spans.projected + AR_h = (b_h**2.)/S_h + taper_h = vehicle.wings['horizontal_stabilizer'].spans.projected + sweep_h = vehicle.wings['horizontal_stabilizer'].sweeps.quarter_chord + mac_h = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic + t_c_h = vehicle.wings['horizontal_stabilizer'].thickness_to_chord + l_w2h = vehicle.wings['horizontal_stabilizer'].origin[0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings['main_wing'].aerodynamic_center[0] #used for fuselage weight + wt_tail_horizontal = tail_horizontal(S_h, AR_h, sweep_h, q_c, taper_h, t_c_h,Nult,TOW) + + vehicle.wings['horizontal_stabilizer'].mass_properties.mass = wt_tail_horizontal + + #vertical stabilizer + if not vehicle.wings.has_key('vertical_stabilizer'): + output_3 = Data() + output_3.wt_tail_vertical = 0.0 + + S_v = 0.0 + warnings.warn("There is no Vertical Tail Weight being added to the Configuration", stacklevel=1) + + else: + S_v = vehicle.wings['vertical_stabilizer'].areas.reference + b_v = vehicle.wings['vertical_stabilizer'].spans.projected + AR_v = (b_v**2.)/S_v + taper_v = vehicle.wings['vertical_stabilizer'].taper + t_c_v = vehicle.wings['vertical_stabilizer'].thickness_to_chord + sweep_v = vehicle.wings['vertical_stabilizer'].sweeps.quarter_chord + t_tail = vehicle.wings['vertical_stabilizer'].t_tail + output_3 = tail_vertical(S_v, AR_v, sweep_v, q_c, taper_v, t_c_v, Nult,TOW,t_tail) + + vehicle.wings['vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical + + if not vehicle.has_key('fuselages.fuselage'): + S_fus = vehicle.fuselages['fuselage'].areas.wetted + diff_p_fus = vehicle.fuselages['fuselage'].differential_pressure + w_fus = vehicle.fuselages['fuselage'].width + h_fus = vehicle.fuselages['fuselage'].heights.maximum + l_fus = vehicle.fuselages['fuselage'].lengths.structure + V_fuse = vehicle.fuselages['fuselage'].mass_properties.volume + V_int = vehicle.fuselages['fuselage'].mass_properties.internal_volume + num_seats = vehicle.fuselages['fuselage'].number_coach_seats + #calculate fuselage weight + wt_fuselage = fuselage(S_fus, Nult, TOW, w_fus, h_fus, l_fus, l_w2h, q_c, V_fuse, diff_p_fus) + else: + print 'got here' + warnings.warn('There is no Fuselage weight being added to the vehicle', stacklevel=1) + + #landing gear + if not vehicle.has_key('landing_gear'): + warnings.warn('There is no Landing Gear weight being added to the vehicle', stacklevel=1) + wt_landing_gear = Data() + wt_landing_gear.main = 0.0 + wt_landing_gear.nose = 0.0 + + else: + landing_gear_component = vehicle.landing_gear #landing gear previously defined + strut_length_main = landing_gear_component.main.strut_length + strut_length_nose = landing_gear_component.nose.strut_length + wt_landing_gear = landing_gear(landing_weight, Nult, strut_length_main, strut_length_nose) + + landing_gear_component.main.mass_properties.mass = wt_landing_gear.main + landing_gear_component.nose.mass_properties.mass = wt_landing_gear.nose + + if not vehicle.has_key('avionics'): + warnings.warn('There is no avionics weight being added to the vehicle; many weight correlations are dependant on this', stacklevel=1) + avionics = SUAVE.Components.Energy.Peripherals.Avionics() + W_uav = 0. + + else: + avionics = vehicle.avionics + W_uav = avionics.mass_properties.uninstalled + + has_air_conditioner = 0 + if vehicle.has_key('air_conditioner'): + has_air_conditioner = 1 + + # Calculating Empty Weight of Aircraft + output_2 = systems(W_uav,V_fuel, V_fuel_int, N_tank, num_eng, l_fus, b, TOW, Nult, num_seats, mach_number, has_air_conditioner) + + # Calculate the equipment empty weight of the aircraft + + wt_empty = (wt_wing + wt_fuselage + wt_landing_gear.main+wt_landing_gear.nose + wt_propulsion + output_2.wt_systems + \ + wt_tail_horizontal + output_3.wt_tail_vertical) + vehicle.fuselages['fuselage'].mass_properties.mass = wt_fuselage + + # packup outputs + output = payload(TOW, wt_empty, num_pax,wt_cargo) + output.wing = wt_wing + output.fuselage = wt_fuselage + output.propulsion = wt_propulsion + output.landing_gear_main = wt_landing_gear.main + output.landing_gear_nose = wt_landing_gear.nose + output.horizontal_tail = wt_tail_horizontal + output.vertical_tail = output_3.wt_tail_vertical + + output.systems = output_2.wt_systems + output.systems_breakdown = Data() + output.systems_breakdown.control_systems = output_2.wt_flt_ctrl + output.systems_breakdown.hydraulics = output_2.wt_hyd_pnu + output.systems_breakdown.avionics = output_2.wt_avionics + output.systems_breakdown.electrical = output_2.wt_elec + output.systems_breakdown.air_conditioner = output_2.wt_ac + output.systems_breakdown.furnish = output_2.wt_furnish + output.systems_breakdown.fuel_system = output_2.wt_fuel_sys + #define weights components + + control_systems = SUAVE.Components.Physical_Component() + electrical_systems= SUAVE.Components.Physical_Component() + passengers = SUAVE.Components.Physical_Component() + furnishings = SUAVE.Components.Physical_Component() + + apu = SUAVE.Components.Physical_Component() + hydraulics = SUAVE.Components.Physical_Component() + + #assign output weights to objects + control_systems.mass_properties.mass = output.systems_breakdown.control_systems + electrical_systems.mass_properties.mass = output.systems_breakdown.electrical + passengers.mass_properties.mass = output.pax + output.bag + furnishings.mass_properties.mass = output.systems_breakdown.furnish + avionics.mass_properties.mass = output.systems_breakdown.avionics + hydraulics.mass_properties.mass = output.systems_breakdown.hydraulics + + if has_air_conditioner: + vehicle.air_conditioner.mass_properties.mass = output.systems_breakdown.air_conditioner + + #assign components to vehicle + vehicle.control_systems = control_systems + vehicle.electrical_systems = electrical_systems + vehicle.avionics = avionics + vehicle.furnishings = furnishings + vehicle.passenger_weights = passengers + + vehicle.apu = apu + vehicle.hydraulics = hydraulics + vehicle.landing_gear = landing_gear_component + + #note; air conditioner optional, and weight is added to the air_conditioner object directly + return output \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/fuselage.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/fuselage.py new file mode 100644 index 0000000000..b951729541 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/fuselage.py @@ -0,0 +1,62 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# fuselage.py +# +# Created: Feb 2018, M. Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Units +import numpy as np + +# ---------------------------------------------------------------------- +# Fuselage +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-General_Aviation +def fuselage(S_fus, Nult, TOW, w_fus, h_fus, l_fus, l_ht, q_c, V_fuse, diff_p_fus): + """ + Calculate the weight of a fuselage for a GA aircraft + + Source: Raymer: Aircraft Design, a Conceptual Approach (pages 460-461 in 4th edition) + + Inputs: + S_f - fuselage wetted area [meters**2] + Nult - ultimate load of the aircraft [dimensionless]] + TOW - maximum takeoff weight of the aircraft [kilograms] + w_fus - width of the fuselage [meters] + h_fus - height of the fuselage [meters] + l_fus - length of the fuselage [meters] + l_ht - length of tail arm [meters] + q_c - dynamic pressure at cruise [Pascals] + V_fuse - volume of pressurized cabin [meters**3] + diff_p_fus - Maximum fuselage pressure differential [Pascals] + + + + Outputs: + weight - weight of the fuselage [kilograms] + + Assumptions: + fuselage for a general aviation type aircraft + """ + # unpack inputs + + d_fus = (h_fus+w_fus)/2. #take average as diameter + d_str = .025*d_fus+1.*Units.inches #obtained from http://homepage.ntlworld.com/marc.barbour/structures.html + diff_p = diff_p_fus / (Units.force_pound / Units.ft**2.) # Convert Pascals to lbs/ square ft + width = w_fus / Units.ft # Convert meters to ft + height = h_fus / Units.ft # Convert meters to ft + tail_arm = np.abs(l_ht)/Units.ft + V_p = V_fuse/(Units.ft**3) + length = l_fus / Units.ft # Convert meters to ft + weight = TOW / Units.lb # Convert kg to lbs + area = S_fus / (Units.ft**2.) # Convert square meters to square ft + q = q_c /(Units.force_pound / Units.ft**2.) + + #Calculate weight of wing for traditional aircraft vertical tail without rudder + fuselage_weight = .052*(area**1.086)*((Nult*weight)**.177)*(tail_arm**(-.051))*((l_fus/d_str)**(-.072))*(q**.241)+11.9*((V_fuse* diff_p)**.271) + + weight = fuselage_weight*Units.lbs #convert to kg + return weight \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/landing_gear.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/landing_gear.py new file mode 100644 index 0000000000..bc6c1426f9 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/landing_gear.py @@ -0,0 +1,48 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# landing_gear.py +# +# Created: Feb 2018, M. Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Data,Units +import numpy as np + +# ---------------------------------------------------------------------- +# Landing Gear +# ---------------------------------------------------------------------- + +## @ingroup Methods-Weights-Correlations-General_Aviation +def landing_gear(landing_weight, Nult, strut_length_main, strut_length_nose): + """ + Calculate the weight of the landing gear + + Source: Raymer- Aircraft Design: a Conceptual Approach (pg 460 in 4th edition) + + Inputs: + Nult - ultimate landing load factor + landing_weight- landing weight of the aircraft [kilograms] + + Outputs: + weight - weight of the landing gear [kilograms] + + Assumptions: + calculating the landing gear weight based on the landing weight, load factor, and strut length + """ + + #unpack + W_l = landing_weight/Units.lbs + l_n = strut_length_nose/Units.inches + l_m = strut_length_main/Units.inches + main_weight = .095*((Nult*W_l)**.768)*(l_m/12.)**.409 + nose_weight = .125*((Nult*W_l)**.566)*(l_n/12.)**.845 + + #pack outputs + output = Data + output.main = main_weight*Units.lbs + output.nose = nose_weight*Units.lbs + + return output \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py new file mode 100644 index 0000000000..25392eb819 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py @@ -0,0 +1,52 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# payload.py +# +# Created: Feb 2018, M. Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Units, Data + +# ---------------------------------------------------------------------- +# Payload +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-General_Aviation +def payload(TOW, empty, num_pax, wt_cargo, wt_passenger = 225.*Units.lbs,wt_baggage = 0.): + """ + Calculate the weight of the payload and the resulting fuel mass + + Inputs: + TOW - [kilograms] + wt_empty - Operating empty weight of the aircraft [kilograms] + num_pax - number of passengers on the aircraft [dimensionless] + wt_cargo - weight of cargo being carried on the aircraft [kilogram] + wt_passenger - weight of each passenger on the aircraft [kilograms] + wt_baggage - weight of the baggage for each passenger [kilograms] + + + Outputs: + output - a data dictionary with fields: + payload - weight of the passengers plus baggage and paid cargo [kilograms] + pax - weight of all the passengers [kilograms] + bag - weight of all the baggage [kilograms] + fuel - weight of the fuel carried [kilograms] + empty - operating empty weight of the aircraft [kilograms] + + """ + + # process + wt_pax = wt_passenger * num_pax + wt_bag = wt_baggage * num_pax + wt_payload = wt_pax + wt_bag + wt_cargo + + # packup outputs + output = Data() + output.payload = wt_payload + output.pax = wt_pax + output.bag = wt_bag + output.empty = empty + + return output \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/systems.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/systems.py new file mode 100644 index 0000000000..4b956d6571 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/systems.py @@ -0,0 +1,90 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# systems.py +# +# Created: Feb 2018, M. Vegh +# Modified: + + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Units, Data + +# ---------------------------------------------------------------------- +# Systems +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-General_Aviation +def systems(W_uav, V_fuel, V_int, N_tank, N_eng, l_fuselage, span, TOW, Nult, num_seats, mach_number, has_air_conditioner=1): + """ output = SUAVE.Methods.Weights.Correlations.General_Avation.systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type) + Calculate the weight of the different engine systems on the aircraft + + Source: + Raymer, Aircraft Design: A Conceptual Approach (pg 461 in 4th edition) + + Inputs: + V_fuel - total fuel volume [meters**3] + V_int - internal fuel volume [meters**3] + N_tank - number of fuel tanks [dimensionless] + N_eng - number of engines [dimensionless] + span - wingspan [meters] + TOW - gross takeoff weight of the aircraft [kg] + num_seats - total number of seats on the aircraft [dimensionless] + mach_number - mach number [dimensionless] + has_air_conditioner - integer of 1 if the vehicle has ac, 0 if not + + Outputs: + output - a data dictionary with fields: + wt_flt_ctrl - weight of the flight control system [kilograms] + wt_apu - weight of the apu [kilograms] + wt_hyd_pnu - weight of the hydraulics and pneumatics [kilograms] + wt_avionics - weight of the avionics [kilograms] + wt_opitems - weight of the optional items based on the type of aircraft [kilograms] + wt_elec - weight of the electrical items [kilograms] + wt_ac - weight of the air conditioning and anti-ice system [kilograms] + wt_furnish - weight of the furnishings in the fuselage [kilograms] + """ + # unpack inputs + + Q_tot = V_fuel/Units.gallons + Q_int = V_int/Units.gallons + + l_fus = l_fuselage / Units.ft # Convert meters to ft + b_wing = span/Units.ft + + W_0 = TOW/Units.lb + + #fuel system + fuel_sys_wt = 2.49*(Q_tot**.726)*((Q_tot/(Q_tot+Q_int))**.363)*(N_tank**.242)*(N_eng**.157)*Units.lb + + #flight controls + flt_ctrl_wt = .053*(l_fus**1.536)*(b_wing**.371)*((Nult*W_0**(10.**(-4.)))**.8)*Units.lb + #Hydraulics & Pneumatics Group Wt + hyd_pnu_wt = (.001*W_0) * Units.lb + + #avionics weight + avionics_wt = 2.117*((W_uav/Units.lbs)**.933)*Units.lb + + # Electrical Group Wt + elec_wt = 12.57*((avionics_wt/Units.lb +fuel_sys_wt/Units.lb)**.51)*Units.lb + + # Environmental Control + ac_wt = has_air_conditioner*.265*(W_0**.52)*((1. * num_seats)**.68)*((avionics_wt/Units.lb)**.17)*(mach_number**.08)*Units.lb + + # Furnishings Group Wt + furnish_wt = (.0582*W_0-65.)*Units.lb + + # packup outputs + output = Data() + output.wt_flt_ctrl = flt_ctrl_wt + output.wt_hyd_pnu = hyd_pnu_wt + output.wt_avionics = avionics_wt + output.wt_elec = elec_wt + output.wt_ac = ac_wt + output.wt_furnish = furnish_wt + output.wt_fuel_sys = fuel_sys_wt + output.wt_systems = output.wt_flt_ctrl + output.wt_hyd_pnu \ + + output.wt_ac + output.wt_avionics + output.wt_elec \ + + output.wt_furnish +output.wt_fuel_sys + + return output \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_horizontal.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_horizontal.py new file mode 100644 index 0000000000..af0d5f4e62 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_horizontal.py @@ -0,0 +1,50 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# tail_horizontal.py +# +# Created: Feb 2018, M Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Units +import numpy as np + +# ---------------------------------------------------------------------- +# Tail Horizontal +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-General_Aviation +def tail_horizontal(S_h, AR_h, sweep_h, q_c, taper_h, t_c_h,Nult,TOW): + """ + Calculate the weight of the horizontal tail for a General Aviation-type aircraft + + Source: + Aircraft Design: A Conceptual Approach by Raymer (pg 460 in 4th edition) + + + Inputs: + S_h = trapezoidal area of horizontal tail [meters**2] + Ar_h = aspect ratio of horizontal tail [dimensionless] + sweep_h = quarter chord sweep of the horizontal tail [radians] + q_c = dynamic pressure at cruise [Pascals] + + + Outputs: + weight - weight of the horizontal tail [kilograms] + + Assumptions: + calculated weight of the horizontal tail including the elevator + Assume that the elevator is 25% of the horizontal tail + + """ + # unpack inputs + W_0 = TOW / Units.lb # Convert kg to lbs + S_ht = S_h/ Units.ft**2 # Convert from meters squared to ft squared + q = q_c /(Units.force_pound / Units.ft**2.) + + #Calculate weight of wing for traditional aircraft horizontal tail + weight_English = .016*((Nult*W_0)**.414)*(q**.168)*(S_ht**.896)*((100.*t_c_h/np.cos(sweep_h))**(-.12))*((AR_h/(np.cos(sweep_h)**2))**.043)*(taper_h**(-.02)) + weight = weight_English * Units.lbs # Convert from lbs to kg + + return weight \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_vertical.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_vertical.py new file mode 100644 index 0000000000..65fb3e0fe0 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_vertical.py @@ -0,0 +1,65 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# tail_vertical.py +# +# Created: Feb 2018, M. Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Units, Data +import numpy as np + +# ---------------------------------------------------------------------- +# Tail Vertical +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-General_Aviation +def tail_vertical(S_v, AR_v, sweep_v, q_c, taper_v, t_c_v, Nult,TOW,t_tail, rudder_fraction = 0.25): + """ + Calculate the weight of the vertical fin of an aircraft without the weight of the rudder and then calculate the weight of the rudder + + Source: + Raymer, Aircraft Design: A Conceptual Approach (pg 460 in 4th edition) + + Inputs: + S_v - area of the vertical tail (combined fin and rudder) [meters**2] + M_w -mass of wing [kilograms] + AR_v -aspect ratio of vertial tail [dimensionless] + sweep_v - sweep angle of the vertical tail [radians] + q_c - dynamic pressure at cruise [Pascals] + taper_v - taper ratio of vertical tail [dimensionless] + t_c_v -thickness to chord ratio of wing [dimensionless] + Nult - ultimate load of the aircraft [dimensionless] + TOW - maximum takeoff weight of the aircraft [kilograms] + S_gross_w - wing gross area [meters**2] + t_tail - flag to determine if aircraft has a t-tail [dimensionless] + rudder_fraction - fraction of the vertical tail that is the rudder [dimensionless] + + Outputs: + output - a dictionary with outputs: + wt_tail_vertical - weight of the vertical fin portion of the vertical tail [kilograms] + + Assumptions: + Vertical tail weight is the weight of the vertical fin without the rudder weight. + + """ + # unpack inputs + W_0 = TOW / Units.lb # Convert kg to lbs + S_vt = S_v/ Units.ft**2 # Convert from meters squared to ft squared + q = q_c /(Units.force_pound / Units.ft**2.) + + # Determine weight of the vertical portion of the tail + if t_tail == "yes": + T_tail_factor = 1.# Weight of vertical portion of the T-tail is 25% more than a conventional tail + else: + T_tail_factor = 0. + + # Calculate weight of wing for traditional aircraft vertical tail without rudder + tail_vert_English = .073*(1+.2*T_tail_factor)*((Nult*W_0)**(.376))*(q**.122)*(S_vt**.873)*((100.*t_c_v/np.cos(sweep_v))**(-.49))*((AR_v/(np.cos(sweep_v)**2.))**.357)*(taper_v**.039) + + # packup outputs + output = Data() + output.wt_tail_vertical = tail_vert_English * Units.lbs # Convert from lbs to kg + + return output diff --git a/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py new file mode 100644 index 0000000000..b57ee1d27a --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py @@ -0,0 +1,53 @@ +## @ingroup Methods-Weights-Correlations-General_Aviation +# wing_main.py +# +# Created: Feb 2018, M. Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Units +import numpy as np + +# ---------------------------------------------------------------------- +# Wing Main +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-General_Aviation +def wing_main(S_wing, m_fuel, AR_w, sweep_w, q_c, taper_w, t_c_w,Nult,TOW): + """ + Calculate the weight of the main wing of an aircraft + + Source: + Raymer, Aircraft Design: A Conceptual Approach (pg 460 in 4th edition) + + Inputs: + S_wing- area of the main wing [meters**2] + m_fuel - predicted weight of fuel in the wing [kilograms] + AR_w -aspect ratio of main wing [dimensionless] + sweep_w - quarter chord sweep of the main wing [radians] + q_c - dynamic pressure at cruise [Pascals] + taper_w - taper ratio of wing [dimensionless] + t_c_w -thickness to chord ratio of wing [dimensionless] + Nult - ultimate load of the aircraft [dimensionless] + TOW - maximum takeoff weight of the aircraft [kilograms] + + Outputs: + output - a dictionary with outputs: + wt_main_wing - weight of the vertical fin portion of the vertical tail [kilograms] + """ + # unpack inputs + + W_0 = TOW / Units.lb # Convert kg to lbs + S_w = S_wing/ (Units.ft**2) # Convert from meters squared to ft squared + W_fw = m_fuel/Units.lbs #convert from kg to lbs + q = q_c /(Units.lbs/(Units.ft**2.)) + + # Calculate weight of wing for traditional aircraft vertical tail without rudder + weight_English = .036 * (S_w**.758)*(W_fw**.0035)*((AR_w/(np.cos(sweep_w)**2))**.6)*(q**.006)*(taper_w**.04)*((100.*t_c_w/np.cos(sweep_w))**(-.3))*((Nult*W_0)**.49) + # packup outputs + + weight = weight_English * Units.lbs # Convert from lbs to kg + + return weight diff --git a/trunk/SUAVE/Methods/Weights/Correlations/Propulsion/integrated_propulsion_general_aviation.py b/trunk/SUAVE/Methods/Weights/Correlations/Propulsion/integrated_propulsion_general_aviation.py new file mode 100644 index 0000000000..0eec270497 --- /dev/null +++ b/trunk/SUAVE/Methods/Weights/Correlations/Propulsion/integrated_propulsion_general_aviation.py @@ -0,0 +1,38 @@ +## @ingroup Methods-Weights-Correlations-Propulsion +# integrated_propulsion_general_aviation.py +# +# Created: Feb 2018, M. Vegh +# Modified: + +# ---------------------------------------------------------------------- +# Imports +# ---------------------------------------------------------------------- + +from SUAVE.Core import Units + + +# ---------------------------------------------------------------------- +# Integrated Propulsion +# ---------------------------------------------------------------------- +## @ingroup Methods-Weights-Correlations-Propulsion +def integrated_propulsion_general_aviation(engine_piston,num_eng, engine_wt_factor = 2.575, engine_wt_exp = .922): + """ + Calculate the weight of the entire propulsion system + + Source: + Source: Raymer, Aircraft Design, a Conceptual Approach + + Inputs: + engine_piston - dry weight of a single engine [kilograms] + num_eng - total number of engines on the aircraft [dimensionless] + engine_wt_factor - weight increase factor for entire integrated propulsion system [dimensionless] + + Outputs: + weight - weight of the full propulsion system [kilograms] + + """ + engine_dry = engine_piston/Units.lbs + weight = engine_wt_factor * (engine_dry**engine_wt_exp)*num_eng + mass = weight*Units.lbs #convert to kg + + return mass \ No newline at end of file From 4a074153083d6af3c87bddca563380acacd4bdbf Mon Sep 17 00:00:00 2001 From: WalterMaier Date: Mon, 16 Apr 2018 22:52:40 -0700 Subject: [PATCH 2/6] scramjets now work...thanks github... --- regression/automatic_regression.py | 1 + .../scramjet_network/scramjet_network.py | 24 +++++------ .../Components/Energy/Converters/Combustor.py | 43 ++++++++++--------- .../Energy/Converters/Compression_Nozzle.py | 43 +++++++++++-------- .../SUAVE/Components/Energy/Converters/Ram.py | 6 +-- .../Energy/Converters/Supersonic_Nozzle.py | 2 +- .../Components/Energy/Processes/Thrust.py | 10 ++--- .../Common/Gas_Dynamics/Oblique_Shock.py | 8 ++-- .../Methods/Propulsion/scramjet_sizing.py | 16 ++++--- trunk/SUAVE/Methods/Propulsion/shock_train.py | 8 ++-- 10 files changed, 85 insertions(+), 76 deletions(-) diff --git a/regression/automatic_regression.py b/regression/automatic_regression.py index 3d56b3f58d..d9559f88e3 100644 --- a/regression/automatic_regression.py +++ b/regression/automatic_regression.py @@ -67,6 +67,7 @@ 'scripts/ramjet_network/ramjet_network.py', 'scripts/lifting_line/lifting_line.py', 'scripts/sweeps/test_sweeps.py', + 'scripts/scramjet_network/scramjet_network.py', ] diff --git a/regression/scripts/scramjet_network/scramjet_network.py b/regression/scripts/scramjet_network/scramjet_network.py index 59ea16f3ad..0947f557ca 100644 --- a/regression/scripts/scramjet_network/scramjet_network.py +++ b/regression/scripts/scramjet_network/scramjet_network.py @@ -46,9 +46,9 @@ def energy_network(): # freestream conditions EVAL = conditions.freestream - EVAL.mach_number = ones_1col*3.5 + EVAL.mach_number = ones_1col*4.5 conditions.M = EVAL.mach_number - EVAL.altitude = ones_1col*10000. + EVAL.altitude = ones_1col*20000. atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976() atmo_data = atmosphere.compute_values(EVAL.altitude,0,True) @@ -85,7 +85,7 @@ def energy_network(): SIZE = conditions_sizing.freestream SIZE.mach_number = ones_1col*6.5 conditions_sizing.M = SIZE.mach_number - SIZE.altitude = ones_1col*10000. + SIZE.altitude = ones_1col*20000. atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976() atmo_data = atmosphere.compute_values(SIZE.altitude,0,True) @@ -125,9 +125,9 @@ def energy_network(): # setup scramjet.number_of_engines = 1.0 - scramjet.engine_length = 6.0 - scramjet.nacelle_diameter = 1.3 * Units.meter - scramjet.inlet_diameter = 1.1 * Units.meter + scramjet.engine_length = 4.0 + scramjet.nacelle_diameter = 0.3 * Units.meter + scramjet.inlet_diameter = 0.21 * Units.meter # working fluid scramjet.working_fluid = SUAVE.Attributes.Gases.Air() @@ -172,8 +172,9 @@ def energy_network(): combustor.turbine_inlet_temperature = 2400. combustor.pressure_ratio = 1.0 combustor.area_ratio = 2.0 - combustor.fuel_data = SUAVE.Attributes.Propellants.JP7() - combustor.rayleigh_analyses = True + combustor.fuel_data = SUAVE.Attributes.Propellants.Liquid_H2() + combustor.burner_drag_coefficient = 0.01 + combustor.fuel_equivalency_ratio = 1.0 # add to network scramjet.append(combustor) @@ -206,7 +207,7 @@ def energy_network(): scramjet.thrust = thrust #size the ramjet - scramjet_sizing(scramjet,2.5,10000.0) + scramjet_sizing(scramjet,6.5,20000.0) print "Design thrust :",scramjet.design_thrust print "Sealevel static thrust :",scramjet.sealevel_static_thrust @@ -216,13 +217,12 @@ def energy_network(): F = results_design.thrust_force_vector mdot = results_design.vehicle_mass_rate Isp = results_design.specific_impulse - F_off_design = results_off_design.thrust_force_vector + F_off_design = results_off_design.thrust_force_vector mdot_off_design = results_off_design.vehicle_mass_rate Isp_off_design = results_off_design.specific_impulse #Specify the expected values - expected = Data() - + expected = Data() expected.thrust = 338740.93039999995 expected.mdot = 23.11959727 expected.Isp = 1494.05374047 diff --git a/trunk/SUAVE/Components/Energy/Converters/Combustor.py b/trunk/SUAVE/Components/Energy/Converters/Combustor.py index facc204457..8231dc8bad 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Combustor.py +++ b/trunk/SUAVE/Components/Energy/Converters/Combustor.py @@ -74,9 +74,8 @@ def __defaults__(self): self.axial_fuel_velocity_ratio = 0.0 self.fuel_velocity_ratio = 0.0 self.burner_drag_coefficient = 0.0 - self.specific_heat_constant_pressure = 1510.0 self.absolute_sensible_enthalpy = 0.0 - self.temperature_reference = 273.0 + self.fuel_equivalency_ratio = 1.0 def compute(self,conditions): """ This computes the output values from the input values according to @@ -303,11 +302,13 @@ def compute_supersonic_combustion(self,conditions): # unpacking the values from conditions R = conditions.freestream.gas_specific_constant - + Tref = conditions.freestream.temperature + # unpacking the values from inputs - nozzle = self.inputs.inlet_nozzle - Pt_in = self.inputs.stagnation_pressure - + nozzle = self.inputs.inlet_nozzle + Pt_in = self.inputs.stagnation_pressure + Cp_c = nozzle.specific_heat_at_constant_pressure + # unpacking the values from self htf = self.fuel_data.specific_energy eta_b = self.efficiency @@ -315,10 +316,10 @@ def compute_supersonic_combustion(self,conditions): Vf_V3 = self.fuel_velocity_ratio Cfb = self.burner_drag_coefficient hf = self.absolute_sensible_enthalpy - Cpb = self.specific_heat_constant_pressure - Tref = self.temperature_reference + phi = self.fuel_equivalency_ratio - # compute gamma overburner + # compute gamma and Cp over burner + Cpb = Cp_c*1.45 # Estimate from Heiser and Pratt gamma_b = (Cpb/R)/(Cpb/R-1.) # unpack nozzle input values @@ -327,13 +328,14 @@ def compute_supersonic_combustion(self,conditions): P_in = nozzle.static_pressure # setting stoichiometric fuel-to-air - f = self.fuel_data.stoichiometric_fuel_to_air + f_st = self.fuel_data.stoichiometric_fuel_to_air + f = phi*f_st # compute output velocity, mach and temperature V_out = V_in*(((1.+f*Vfx_V3)/(1.+f))-(Cfb/(2.*(1.+f)))) T_out = ((T_in/(1.+f))*(1.+(1./(Cpb*T_in ))*(eta_b*f*htf+f*hf+f*Cpb*Tref+(1.+f*Vf_V3*Vf_V3)*V_in*V_in/2.))) - V_out*V_out/(2.*Cpb) M_out = V_out/(np.sqrt(gamma_b*R*T_out)) - Tt_out = T_out*(1+(gamma_b-1)/2)*M_out*M_out + Tt_out = T_out*(1.+(gamma_b-1.)/2.)*M_out*M_out # compute the exity static and stagnation conditions ht_out = Cpb*Tt_out @@ -341,15 +343,16 @@ def compute_supersonic_combustion(self,conditions): Pt_out = Pt_in*((((gamma_b+1.)*(M_out**2.))/((gamma_b-1.)*M_out**2.+2.))**(gamma_b/(gamma_b-1.)))*((gamma_b+1.)/(2.*gamma_b*M_out**2.-(gamma_b-1.)))**(1./(gamma_b-1.)) # pack computed quantities into outputs - self.outputs.stagnation_temperature = Tt_out - self.outputs.stagnation_pressure = Pt_out - self.outputs.stagnation_enthalpy = ht_out - self.outputs.fuel_to_air_ratio = f - self.outputs.static_temperature = T_out - self.outputs.static_pressure = P_out - self.outputs.velocity = V_out - self.outputs.mach_number = M_out + self.outputs.stagnation_temperature = Tt_out + self.outputs.stagnation_pressure = Pt_out + self.outputs.stagnation_enthalpy = ht_out + self.outputs.fuel_to_air_ratio = f + self.outputs.static_temperature = T_out + self.outputs.static_pressure = P_out + self.outputs.velocity = V_out + self.outputs.mach_number = M_out self.outputs.specific_heat_constant_pressure = Cpb - self.outputs.isentropic_expansion_factor = gamma_b + self.outputs.isentropic_expansion_factor = gamma_b + __call__ = compute diff --git a/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py b/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py index c3d63f1aa4..947f7c7253 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py +++ b/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py @@ -203,6 +203,7 @@ def compute_scramjet(self,conditions): static_temperature [K] static_enthalpy [J/kg] velocity [m/s] + specific_heat_at_constant_pressure [J/(kg K)] Properties Used: self. @@ -216,10 +217,10 @@ def compute_scramjet(self,conditions): # unpack from conditions gamma = conditions.freestream.isentropic_expansion_factor Cp = conditions.freestream.specific_heat_at_constant_pressure - Po = conditions.freestream.pressure - To = conditions.freestream.temperature - Mo = conditions.freestream.mach_number - Vo = conditions.freestream.velocity + P0 = conditions.freestream.pressure + T0 = conditions.freestream.temperature + M0 = conditions.freestream.mach_number + U0 = conditions.freestream.velocity R = conditions.freestream.gas_specific_constant # unpack from inputs @@ -234,25 +235,31 @@ def compute_scramjet(self,conditions): # compute compressed flow variables # compute inlet conditions, based on geometry and number of shocks - psi, Ptr = shock_train(Mo,gamma,shock_count,theta) + psi, Ptr = shock_train(M0,gamma,shock_count,theta) + + # Compute/Look Up New gamma and Cp values (Future Work) + gamma_c = gamma + Cp_c = Cp # compute outputs - T_out = psi*To - P_out = Po*(psi/(psi*(1.-eta)+eta))**(Cp/R) + T_out = psi*T0 + P_out = P0*(psi/(psi*(1.-eta)+eta))**(Cp_c/R) Pt_out = Ptr*Pt_in - Mach = np.sqrt((2./(gamma-1.))*((To/T_out)*(1.+(gamma-1.)/2.*Mo*Mo)-1.)) - u_out = np.sqrt(Vo*Vo-2.*Cp*To*(psi-1.)) - h_out = Cp*T_out + Mach = np.sqrt((2./(gamma_c-1.))*((T0/T_out)*(1.+(gamma_c-1.)/2.*M0*M0)-1.)) + u_out = np.sqrt(U0*U0-2.*Cp_c*T0*(psi-1.)) + h_out = Cp_c*T_out Tt_out = Tt_in - ht_out = Cp*Tt_out + ht_out = Cp_c*Tt_out # packing output values - self.outputs.stagnation_temperature = Tt_out - self.outputs.stagnation_pressure = Pt_out - self.outputs.stagnation_enthalpy = ht_out - self.outputs.mach_number = Mach - self.outputs.static_temperature = T_out - self.outputs.static_enthalpy = h_out - self.outputs.static_pressure = P_out + self.outputs.stagnation_temperature = Tt_out + self.outputs.stagnation_pressure = Pt_out + self.outputs.stagnation_enthalpy = ht_out + self.outputs.mach_number = Mach + self.outputs.static_temperature = T_out + self.outputs.static_enthalpy = h_out + self.outputs.static_pressure = P_out + self.outputs.specific_heat_at_constant_pressure = Cp_c + self.outputs.velocity = u_out __call__ = compute diff --git a/trunk/SUAVE/Components/Energy/Converters/Ram.py b/trunk/SUAVE/Components/Energy/Converters/Ram.py index f9e0ea6018..7a07e75250 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Ram.py +++ b/trunk/SUAVE/Components/Energy/Converters/Ram.py @@ -96,7 +96,7 @@ def compute(self,conditions): #unpack from conditions Po = conditions.freestream.pressure To = conditions.freestream.temperature - M = conditions.freestream.mach_number + M = conditions.freestream.mach_number #unpack from inputs working_fluid = self.inputs.working_fluid @@ -112,7 +112,6 @@ def compute(self,conditions): stagnation_temperature = To*(1.+((gamma-1.)/2.*M*M)) stagnation_pressure = Po*((1.+(gamma-1.)/2.*M*M )**(gamma/(gamma-1.))) - #pack computed outputs #pack the values into conditions @@ -122,7 +121,6 @@ def compute(self,conditions): self.outputs.specific_heat_at_constant_pressure = Cp self.outputs.gas_specific_constant = R - #pack the values into outputs conditions.freestream.stagnation_temperature = stagnation_temperature conditions.freestream.stagnation_pressure = stagnation_pressure @@ -130,4 +128,4 @@ def compute(self,conditions): conditions.freestream.specific_heat_at_constant_pressure = Cp conditions.freestream.gas_specific_constant = R - __call__ = compute + __call__ = compute \ No newline at end of file diff --git a/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py b/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py index df51d8bb6c..5172062192 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py +++ b/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py @@ -405,7 +405,7 @@ def compute_scramjet(self,conditions): # compute output properties T_out = T_in*(1.-eta*(1.-((P_out/Po)*(Po/P_in))**(R/Cpe))) u_out = np.sqrt(u_in*u_in+2.*Cpe*(T_in-T_out)) - A_ratio = (1.+f)*(Po/P_out)*(T_out/To)*(Vo/u_out) + A_ratio = (1.+f)*(Po/P_out)*(T_out/To)*(Vo/u_out) M_out = u_out/np.sqrt(gamma*R*T_out) #pack computed quantities into outputs diff --git a/trunk/SUAVE/Components/Energy/Processes/Thrust.py b/trunk/SUAVE/Components/Energy/Processes/Thrust.py index 6fad119aec..9c513c114d 100644 --- a/trunk/SUAVE/Components/Energy/Processes/Thrust.py +++ b/trunk/SUAVE/Components/Energy/Processes/Thrust.py @@ -298,8 +298,8 @@ def compute_stream_thrust(self,conditions): # --------Stream thrust method --------------------------- Sa0 = u0*(1+R*T0/u0**2) - Sa_exit = core_exit_velocity*(1+R*core_exit_temperature/core_exit_velocity**2) - Fsp = ((1+f)*Sa_exit - Sa0 - R*T0/u0*(core_area_ratio-1))/a0 + Sa10 = core_exit_velocity*(1+R*core_exit_temperature/core_exit_velocity**2) + Fsp = ((1+f)*Sa10 - Sa0 - R*T0/u0*(core_area_ratio-1))/a0 #Computing the specific impulse Isp = Fsp*a0*(1+bypass_ratio)/(f*g) @@ -326,7 +326,8 @@ def compute_stream_thrust(self,conditions): self.outputs.non_dimensional_thrust = Fsp self.outputs.core_mass_flow_rate = mdot_core self.outputs.fuel_flow_rate = fuel_flow_rate - self.outputs.power = power + self.outputs.power = power + self.outputs.specific_impulse = Isp def size(self,conditions): """Sizes the core flow for the design condition. @@ -374,7 +375,6 @@ def size(self,conditions): #unpack results Fsp = self.outputs.non_dimensional_thrust - #compute dimensional mass flow rates mdot_core = design_thrust/(Fsp*a0*(1+bypass_ratio)*no_eng*throttle) mdhc = mdot_core/ (np.sqrt(Tref/total_temperature_reference)*(total_pressure_reference/Pref)) @@ -383,8 +383,6 @@ def size(self,conditions): self.mass_flow_rate_design = mdot_core self.compressor_nondimensional_massflow = mdhc - - return def size_stream_thrust(self,conditions): diff --git a/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py b/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py index 67e828d20d..50ca827287 100644 --- a/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py +++ b/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py @@ -85,10 +85,10 @@ def theta_beta_mach(M0,gamma,theta,n=0): c = np.tan(MU)*np.tan(MU) # Calculate shock angle - a = (((gamma-1.)/2.)+((gamma+1.)/2.)*c/2.)*np.tan(theta) - b = (((gamma-1.)/2.)+((gamma+3.)/2.)*c/2.)*np.tan(theta) - d = np.sqrt(((4.*(1.-3.*a*b)**3.)/(27.*a*a*c+9.*a*b-2.))-1.) + a = ((gamma-1.)/2.+(gamma+1.)*c/2.)*np.tan(theta) + b = ((gamma+1.)/2.+(gamma+3.)*c/2.)*np.tan(theta) + d = np.sqrt(((4.*(1.-3.*a*b)**3.)/(27.*a*a*c+9.*a*b-2.)**2)-1.) - beta = np.arctan((b+9.*a*c)/(2.*(1.-3.*a*b))-(d*(27.*a*a*c+9.*a*b-2.))/(6.*a*(1.-3.*a*b))*np.tan(np.pi/3.+1./3.*np.arctan(1./d))) + beta =np.arctan((b+9.*a*c)/(2.*(1.-3.*a*b))-(d*(27.*a**2.*c+9.*a*b-2))/(6.*a*(1.-3.*a*b))*np.tan(n*np.pi/3.+1./3.*np.arctan(1./d))) return beta \ No newline at end of file diff --git a/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py b/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py index 5ce669cde8..460b0bf155 100644 --- a/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py +++ b/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py @@ -73,7 +73,7 @@ def scramjet_sizing(scramjet,mach_number = None, altitude = None, delta_isa = 0, #Creating the network by manually linking the different components #set the working fluid to determine the fluid properties - ram.inputs.working_fluid = scramjet.working_fluid + ram.inputs.working_fluid = scramjet.working_fluid #Flow through the ram ram(conditions) @@ -82,19 +82,21 @@ def scramjet_sizing(scramjet,mach_number = None, altitude = None, delta_isa = 0, inlet_nozzle.inputs = ram.outputs #Flow through the inlet nozzle - inlet_nozzle(conditions) + inlet_nozzle.compute_scramjet(conditions) #link the combustor to the inlet nozzle - combustor.inputs = inlet_nozzle.outputs - + combustor.inputs.stagnation_temperature = inlet_nozzle.outputs.stagnation_temperature + combustor.inputs.stagnation_pressure = inlet_nozzle.outputs.stagnation_pressure + combustor.inputs.inlet_nozzle = inlet_nozzle.outputs + #flow through the high pressor comprresor - combustor.compute_rayleigh(conditions) + combustor.compute_supersonic_combustion(conditions) #link the core nozzle to the combustor core_nozzle.inputs = combustor.outputs #flow through the core nozzle - core_nozzle.compute_limited_geometry(conditions) + core_nozzle.compute_scramjet(conditions) #link the thrust component to the core nozzle thrust.inputs.core_nozzle = core_nozzle.outputs @@ -113,7 +115,7 @@ def scramjet_sizing(scramjet,mach_number = None, altitude = None, delta_isa = 0, thrust.inputs.bypass_ratio = 0.0 thrust.inputs.flow_through_core = 1.0 #scaled constant to turn on core thrust computation thrust.inputs.flow_through_fan = 0.0 #scaled constant to turn on fan thrust computation - thrust.size(conditions) + thrust.size_stream_thrust(conditions) #update the design thrust value scramjet.design_thrust = thrust.total_design diff --git a/trunk/SUAVE/Methods/Propulsion/shock_train.py b/trunk/SUAVE/Methods/Propulsion/shock_train.py index a208235c4c..fac0dabf35 100644 --- a/trunk/SUAVE/Methods/Propulsion/shock_train.py +++ b/trunk/SUAVE/Methods/Propulsion/shock_train.py @@ -48,10 +48,10 @@ def shock_train(M0, gamma, nbr_shocks, theta): while shock_count Date: Tue, 17 Apr 2018 11:19:06 -0700 Subject: [PATCH 3/6] Fixed Scramjet, ready to rumble --- .../scramjet_network/scramjet_network.py | 17 +++++----- .../Energy/Converters/Supersonic_Nozzle.py | 12 ++++--- .../Components/Energy/Networks/Scramjet.py | 7 ++-- .../Components/Energy/Processes/Thrust.py | 33 ++++++++----------- 4 files changed, 33 insertions(+), 36 deletions(-) diff --git a/regression/scripts/scramjet_network/scramjet_network.py b/regression/scripts/scramjet_network/scramjet_network.py index 0947f557ca..f152f4a02c 100644 --- a/regression/scripts/scramjet_network/scramjet_network.py +++ b/regression/scripts/scramjet_network/scramjet_network.py @@ -151,7 +151,7 @@ def energy_network(): inlet_nozzle.tag = 'inlet_nozzle' # setup - inlet_nozzle.polytropic_efficiency = 1.0 + inlet_nozzle.polytropic_efficiency = 0.90 inlet_nozzle.pressure_ratio = 1.0 inlet_nozzle.compressibility_effects = 3.0 inlet_nozzle.compression_levels = 3.0 @@ -168,8 +168,7 @@ def energy_network(): combustor.tag = 'combustor' # setup - combustor.efficiency = 1.0 - combustor.turbine_inlet_temperature = 2400. + combustor.efficiency = 0.90 combustor.pressure_ratio = 1.0 combustor.area_ratio = 2.0 combustor.fuel_data = SUAVE.Attributes.Propellants.Liquid_H2() @@ -187,8 +186,8 @@ def energy_network(): nozzle.tag = 'core_nozzle' # setup - nozzle.polytropic_efficiency = 1.0 - nozzle.pressure_ratio = 1.0 + nozzle.polytropic_efficiency = 0.9 + nozzle.pressure_expansion = 1.1 # add to network scramjet.append(nozzle) @@ -201,7 +200,7 @@ def energy_network(): thrust.tag ='thrust' # setup - thrust.total_design = scramjet.number_of_engines*169370.4652 * Units.N + thrust.total_design = scramjet.number_of_engines*180000.0 * Units.N # add to network scramjet.thrust = thrust @@ -223,9 +222,9 @@ def energy_network(): #Specify the expected values expected = Data() - expected.thrust = 338740.93039999995 - expected.mdot = 23.11959727 - expected.Isp = 1494.05374047 + expected.thrust = 180000.0 + expected.mdot = 7.8394948 + expected.Isp = 2340.53651671 #error data function error = Data() diff --git a/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py b/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py index 5172062192..03fd47a790 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py +++ b/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py @@ -69,7 +69,8 @@ def __defaults__(self): self.outputs.stagnation_pressure = 0. self.outputs.stagnation_enthalpy = 0. self.max_area_ratio = 2. - self.min_area_ratio = 1.35 + self.min_area_ratio = 1.35 + self.pressure_expansion = 1.0 @@ -395,14 +396,15 @@ def compute_scramjet(self,conditions): P_in = self.inputs.static_pressure u_in = self.inputs.velocity f = self.inputs.fuel_to_air_ratio - P_out = Po - + Cpe = self.inputs.specific_heat_constant_pressure + gamma = self.inputs.isentropic_expansion_factor + # unpack from self eta = self.polytropic_efficiency - Cpe = self.inputs.specific_heat_constant_pressure - gamma = self.inputs.isentropic_expansion_factor + p10_p0 = self.pressure_expansion # compute output properties + P_out = Po*p10_p0 T_out = T_in*(1.-eta*(1.-((P_out/Po)*(Po/P_in))**(R/Cpe))) u_out = np.sqrt(u_in*u_in+2.*Cpe*(T_in-T_out)) A_ratio = (1.+f)*(Po/P_out)*(T_out/To)*(Vo/u_out) diff --git a/trunk/SUAVE/Components/Energy/Networks/Scramjet.py b/trunk/SUAVE/Components/Energy/Networks/Scramjet.py index d53a0716dd..55f38e6fe4 100644 --- a/trunk/SUAVE/Components/Energy/Networks/Scramjet.py +++ b/trunk/SUAVE/Components/Energy/Networks/Scramjet.py @@ -27,8 +27,11 @@ class Scramjet(Propulsor): """ This is a scramjet for hypersonic flight. Assumptions: - None - + Currrent Implements Stream Function Method + Combustion, Thermochemical Properties are estimated (HAP in below reference unavailable) + Assumes no spillage drag at the momement + Shock-BL Interaction negected + Source: Most of the componentes come from this book: Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., diff --git a/trunk/SUAVE/Components/Energy/Processes/Thrust.py b/trunk/SUAVE/Components/Energy/Processes/Thrust.py index 9c513c114d..61511dbd6b 100644 --- a/trunk/SUAVE/Components/Energy/Processes/Thrust.py +++ b/trunk/SUAVE/Components/Energy/Processes/Thrust.py @@ -264,12 +264,8 @@ def compute_stream_thrust(self,conditions): #unpack the values #unpacking from conditions - gamma = conditions.freestream.isentropic_expansion_factor - Cp = conditions.freestream.specific_heat_at_constant_pressure u0 = conditions.freestream.velocity a0 = conditions.freestream.speed_of_sound - M0 = conditions.freestream.mach_number - p0 = conditions.freestream.pressure T0 = conditions.freestream.temperature g = conditions.freestream.gravity throttle = conditions.propulsion.throttle @@ -280,16 +276,10 @@ def compute_stream_thrust(self,conditions): total_temperature_reference = self.inputs.total_temperature_reference total_pressure_reference = self.inputs.total_pressure_reference core_nozzle = self.inputs.core_nozzle - fan_nozzle = self.inputs.fan_nozzle core_exit_temperature = core_nozzle.temperature - fan_exit_velocity = self.inputs.fan_nozzle.velocity - core_exit_velocity = self.inputs.core_nozzle.velocity - fan_area_ratio = self.inputs.fan_nozzle.area_ratio - core_area_ratio = self.inputs.core_nozzle.area_ratio + core_exit_velocity = core_nozzle.velocity + core_area_ratio = core_nozzle.area_ratio no_eng = self.inputs.number_of_engines - bypass_ratio = self.inputs.bypass_ratio - flow_through_core = self.inputs.flow_through_core #scaled constant to turn on core thrust computation - flow_through_fan = self.inputs.flow_through_fan #scaled constant to turn on fan thrust computation #unpacking from self Tref = self.reference_temperature @@ -302,20 +292,20 @@ def compute_stream_thrust(self,conditions): Fsp = ((1+f)*Sa10 - Sa0 - R*T0/u0*(core_area_ratio-1))/a0 #Computing the specific impulse - Isp = Fsp*a0*(1+bypass_ratio)/(f*g) + Isp = Fsp*a0/(f*g) #Computing the TSFC - TSFC = f/(Fsp*a0) + TSFC = f*g/(Fsp*a0) #computing the core mass flow mdot_core = mdhc*np.sqrt(Tref/total_temperature_reference)*(total_pressure_reference/Pref) #computing the dimensional thrust - FD2 = Fsp*a0*(1+bypass_ratio)*mdot_core*no_eng*throttle + FD2 = Fsp*a0*mdot_core*no_eng*throttle #fuel flow rate a = np.array([0.]) - fuel_flow_rate = np.fmax(0.1019715*FD2*TSFC/3600,a) #use units package for the constants + fuel_flow_rate = np.fmax(FD2*TSFC/g,a) #use units package for the constants #computing the power power = FD2*u0 @@ -413,15 +403,18 @@ def size_stream_thrust(self,conditions): total_design [N] - Design thrust """ - #unpack inputs + # Unpack Inputs + + # Unpack Conditions a0 = conditions.freestream.speed_of_sound throttle = 1.0 - #unpack from self - bypass_ratio = self.inputs.bypass_ratio + # Unpack from self Tref = self.reference_temperature Pref = self.reference_pressure design_thrust = self.total_design + + # Unpack from Inputs total_temperature_reference = self.inputs.total_temperature_reference # low pressure turbine output for turbofan total_pressure_reference = self.inputs.total_pressure_reference no_eng = self.inputs.number_of_engines @@ -433,7 +426,7 @@ def size_stream_thrust(self,conditions): Fsp = self.outputs.non_dimensional_thrust #compute dimensional mass flow rates - mdot_core = design_thrust/(Fsp*a0*(1+bypass_ratio)*no_eng*throttle) + mdot_core = design_thrust/(Fsp*a0*no_eng*throttle) mdhc = mdot_core/ (np.sqrt(Tref/total_temperature_reference)*(total_pressure_reference/Pref)) #pack outputs From 1571af0ea3df41e9c842fd6925ad59587c419f79 Mon Sep 17 00:00:00 2001 From: WalterMaier Date: Sat, 21 Apr 2018 20:54:34 -0700 Subject: [PATCH 4/6] fixing pull request comments --- .../scramjet_network/scramjet_network.py | 82 +++++++++---------- .../Components/Energy/Converters/Combustor.py | 8 +- .../Energy/Converters/Compression_Nozzle.py | 5 +- .../Energy/Converters/Supersonic_Nozzle.py | 14 ++-- .../Components/Energy/Networks/Scramjet.py | 9 +- .../Components/Energy/Processes/Thrust.py | 13 +-- .../Common/Gas_Dynamics/Oblique_Shock.py | 4 +- 7 files changed, 68 insertions(+), 67 deletions(-) diff --git a/regression/scripts/scramjet_network/scramjet_network.py b/regression/scripts/scramjet_network/scramjet_network.py index f152f4a02c..d0673aec93 100644 --- a/regression/scripts/scramjet_network/scramjet_network.py +++ b/regression/scripts/scramjet_network/scramjet_network.py @@ -1,4 +1,4 @@ -# sramjet_network.py +# scramjet_network.py # # Created: April 2018, W. Maier # Modified: @@ -45,28 +45,28 @@ def energy_network(): conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics() # freestream conditions - EVAL = conditions.freestream - EVAL.mach_number = ones_1col*4.5 - conditions.M = EVAL.mach_number - EVAL.altitude = ones_1col*20000. + eval = conditions.freestream + eval.mach_number = ones_1col*4.5 + conditions.M = eval.mach_number + eval.altitude = ones_1col*20000. atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976() - atmo_data = atmosphere.compute_values(EVAL.altitude,0,True) + atmo_data = atmosphere.compute_values(eval.altitude,0,True) working_fluid = SUAVE.Attributes.Gases.Air() - - EVAL.pressure = ones_1col*atmo_data.pressure - EVAL.temperature = ones_1col*atmo_data.temperature - EVAL.density = ones_1col*atmo_data.density - EVAL.dynamic_viscosity = ones_1col* atmo_data.dynamic_viscosity - EVAL.gravity = ones_1col*9.81 - EVAL.isentropic_expansion_factor = working_fluid.compute_gamma(EVAL.temperature,EVAL.pressure) - EVAL.Cp = working_fluid.compute_cp(EVAL.temperature,EVAL.pressure) - EVAL.R = working_fluid.gas_specific_constant - EVAL.speed_of_sound = ones_1col* atmo_data.speed_of_sound - EVAL.velocity = conditions.M * EVAL.speed_of_sound - conditions.velocity = conditions.M * EVAL.speed_of_sound - conditions.q = 0.5*EVAL.density*conditions.velocity**2 - conditions.g0 = EVAL.gravity + + eval.pressure = ones_1col*atmo_data.pressure + eval.temperature = ones_1col*atmo_data.temperature + eval.density = ones_1col*atmo_data.density + eval.dynamic_viscosity = ones_1col* atmo_data.dynamic_viscosity + eval.gravity = ones_1col* SUAVE.Attributes.Planets.Earth().sea_level_gravity + eval.isentropic_expansion_factor = working_fluid.compute_gamma(eval.temperature,eval.pressure) + eval.Cp = working_fluid.compute_cp(eval.temperature,eval.pressure) + eval.R = working_fluid.gas_specific_constant + eval.speed_of_sound = ones_1col* atmo_data.speed_of_sound + eval.velocity = conditions.M * eval.speed_of_sound + conditions.velocity = conditions.M * eval.speed_of_sound + conditions.q = 0.5*eval.density*conditions.velocity**2 + conditions.g0 = eval.gravity # propulsion conditions conditions.propulsion.throttle = ones_1col*1.0 @@ -82,28 +82,28 @@ def energy_network(): conditions_sizing = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics() # freestream conditions - SIZE = conditions_sizing.freestream - SIZE.mach_number = ones_1col*6.5 - conditions_sizing.M = SIZE.mach_number - SIZE.altitude = ones_1col*20000. + size = conditions_sizing.freestream + size.mach_number = ones_1col*6.5 + conditions_sizing.M = size.mach_number + size.altitude = ones_1col*20000. atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976() - atmo_data = atmosphere.compute_values(SIZE.altitude,0,True) + atmo_data = atmosphere.compute_values(size.altitude,0,True) working_fluid = SUAVE.Attributes.Gases.Air() - SIZE.pressure = ones_1col*atmo_data.pressure - SIZE.temperature = ones_1col*atmo_data.temperature - SIZE.density = ones_1col*atmo_data.density - SIZE.dynamic_viscosity = ones_1col*atmo_data.dynamic_viscosity - SIZE.gravity = ones_1col*9.81 - SIZE.isentropic_expansion_factor = working_fluid.compute_gamma(SIZE.temperature,SIZE.pressure) - SIZE.Cp = working_fluid.compute_cp(SIZE.temperature,SIZE.pressure) - SIZE.R = working_fluid.gas_specific_constant - SIZE.speed_of_sound = ones_1col * atmo_data.speed_of_sound - SIZE.velocity = conditions_sizing.M * SIZE.speed_of_sound - conditions_sizing.velocity = conditions_sizing.M * SIZE.speed_of_sound - conditions_sizing.q = 0.5*SIZE.density*conditions_sizing.velocity**2 - conditions_sizing.g0 = SIZE.gravity + size.pressure = ones_1col*atmo_data.pressure + size.temperature = ones_1col*atmo_data.temperature + size.density = ones_1col*atmo_data.density + size.dynamic_viscosity = ones_1col*atmo_data.dynamic_viscosity + size.gravity = ones_1col*SUAVE.Attributes.Planets.Earth().sea_level_gravity + size.isentropic_expansion_factor = working_fluid.compute_gamma(size.temperature,size.pressure) + size.Cp = working_fluid.compute_cp(size.temperature,size.pressure) + size.R = working_fluid.gas_specific_constant + size.speed_of_sound = ones_1col * atmo_data.speed_of_sound + size.velocity = conditions_sizing.M * size.speed_of_sound + conditions_sizing.velocity = conditions_sizing.M * size.speed_of_sound + conditions_sizing.q = 0.5*size.density*conditions_sizing.velocity**2 + conditions_sizing.g0 = size.gravity # propulsion conditions conditions_sizing.propulsion.throttle = ones_1col*1.0 @@ -186,8 +186,8 @@ def energy_network(): nozzle.tag = 'core_nozzle' # setup - nozzle.polytropic_efficiency = 0.9 - nozzle.pressure_expansion = 1.1 + nozzle.polytropic_efficiency = 0.9 + nozzle.pressure_expansion_ratio = 1.1 # add to network scramjet.append(nozzle) @@ -224,7 +224,7 @@ def energy_network(): expected = Data() expected.thrust = 180000.0 expected.mdot = 7.8394948 - expected.Isp = 2340.53651671 + expected.Isp = 2341.33605553 #error data function error = Data() diff --git a/trunk/SUAVE/Components/Energy/Converters/Combustor.py b/trunk/SUAVE/Components/Energy/Converters/Combustor.py index 8231dc8bad..1a7e1ff1b3 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Combustor.py +++ b/trunk/SUAVE/Components/Energy/Converters/Combustor.py @@ -263,7 +263,7 @@ def compute_supersonic_combustion(self,conditions): Source: Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., "Hypersonic Airbreathing Propulsion", 1994 - + Chapter 4 - pgs. 175-180 Inputs: conditions.freestream. @@ -294,7 +294,7 @@ def compute_supersonic_combustion(self,conditions): self.axial_fuel_velocity_ratio [-] self.fuel_velocity_ratio [-] self.burner_drag_coefficient [-] - self.temperature_reference [-] + self.temperature_reference [K] self.absolute_sensible_enthalpy [J/kg] self.specific_heat_constant_pressure [J/(kg K)] """ @@ -329,7 +329,7 @@ def compute_supersonic_combustion(self,conditions): # setting stoichiometric fuel-to-air f_st = self.fuel_data.stoichiometric_fuel_to_air - f = phi*f_st + f = phi*f_st # compute output velocity, mach and temperature V_out = V_in*(((1.+f*Vfx_V3)/(1.+f))-(Cfb/(2.*(1.+f)))) @@ -340,7 +340,7 @@ def compute_supersonic_combustion(self,conditions): # compute the exity static and stagnation conditions ht_out = Cpb*Tt_out P_out = P_in - Pt_out = Pt_in*((((gamma_b+1.)*(M_out**2.))/((gamma_b-1.)*M_out**2.+2.))**(gamma_b/(gamma_b-1.)))*((gamma_b+1.)/(2.*gamma_b*M_out**2.-(gamma_b-1.)))**(1./(gamma_b-1.)) + Pt_out = Pt_in*((((gamma_b+1.)*(M_out**2.))/((gamma_b-1.)*M_out**2.+2.))**(gamma_b/(gamma_b-1.)))*((gamma_b+1.)/(2.*gamma_b*M_out**2.-(gamma_b-1.)))**(1./(gamma_b-1.)) # pack computed quantities into outputs self.outputs.stagnation_temperature = Tt_out diff --git a/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py b/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py index 947f7c7253..b7eeff9b10 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py +++ b/trunk/SUAVE/Components/Energy/Converters/Compression_Nozzle.py @@ -179,7 +179,8 @@ def compute_scramjet(self,conditions): Source: Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., "Hypersonic Airbreathing Propulsion", 1994 - + Chapter 4 - pgs. 175-180 + Inputs: conditions.freestream. isentropic_expansion_factor [-] @@ -209,7 +210,7 @@ def compute_scramjet(self,conditions): self. efficiency [-] shock_count [-] - theta [-] + theta [Rad] """ # unpack the values diff --git a/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py b/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py index 03fd47a790..d975e1d625 100644 --- a/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py +++ b/trunk/SUAVE/Components/Energy/Converters/Supersonic_Nozzle.py @@ -72,8 +72,6 @@ def __defaults__(self): self.min_area_ratio = 1.35 self.pressure_expansion = 1.0 - - def compute(self,conditions): """This computes the output values from the input values according to equations from the source. @@ -339,14 +337,15 @@ def compute_limited_geometry(self,conditions): self.outputs.area_ratio = A_ratio def compute_scramjet(self,conditions): - """This exit conditions of a scramjet. This function may not be necessary completely. + """This computes exit conditions of a scramjet. Assumptions: - Fixed ouput Cp and Gamma + Fixed output Cp and Gamma Source: Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., "Hypersonic Airbreathing Propulsion", 1994 + Chapter 4 - pgs. 175-180 Inputs: conditions.freestream. @@ -376,9 +375,8 @@ def compute_scramjet(self,conditions): Properties Used: self. - eta [-] - Cpe [J/(kg K)] - g_e [-] + polytropic_efficiency [-] + pressure_expansion_ratio [-] """ # unpack values @@ -401,7 +399,7 @@ def compute_scramjet(self,conditions): # unpack from self eta = self.polytropic_efficiency - p10_p0 = self.pressure_expansion + p10_p0 = self.pressure_expansion_ratio # compute output properties P_out = Po*p10_p0 diff --git a/trunk/SUAVE/Components/Energy/Networks/Scramjet.py b/trunk/SUAVE/Components/Energy/Networks/Scramjet.py index 55f38e6fe4..be7dee4731 100644 --- a/trunk/SUAVE/Components/Energy/Networks/Scramjet.py +++ b/trunk/SUAVE/Components/Energy/Networks/Scramjet.py @@ -27,7 +27,7 @@ class Scramjet(Propulsor): """ This is a scramjet for hypersonic flight. Assumptions: - Currrent Implements Stream Function Method + Currently implements Stream Function Method Combustion, Thermochemical Properties are estimated (HAP in below reference unavailable) Assumes no spillage drag at the momement Shock-BL Interaction negected @@ -36,7 +36,7 @@ class Scramjet(Propulsor): Most of the componentes come from this book: Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., "Hypersonic Airbreathing Propulsion", 1994 - + Chapter 4 - pgs. 175-180 """ def __defaults__(self): @@ -156,8 +156,7 @@ def evaluate_thrust(self,state): thrust.inputs.stag_press_lpt_exit = core_nozzle.outputs.stagnation_pressure thrust.inputs.number_of_engines = number_of_engines - thrust.inputs.flow_through_core = 1.0 #scaled constant to turn on core thrust computation - thrust.inputs.flow_through_fan = 0.0 #scaled constant to turn on fan thrust computation + thrust.inputs.flow_through_core = 1.0 #scaled constant to turn on core thrust computation #compute the thrust thrust.compute_stream_thrust(conditions) @@ -179,7 +178,7 @@ def evaluate_thrust(self,state): def size(self,state): - """ Size the sramjet + """ Size the scramjet Assumptions: None diff --git a/trunk/SUAVE/Components/Energy/Processes/Thrust.py b/trunk/SUAVE/Components/Energy/Processes/Thrust.py index 61511dbd6b..3d17879d2d 100644 --- a/trunk/SUAVE/Components/Energy/Processes/Thrust.py +++ b/trunk/SUAVE/Components/Energy/Processes/Thrust.py @@ -64,14 +64,14 @@ def __defaults__(self): self.reference_temperature = 288.15 self.reference_pressure = 1.01325*10**5 self.number_of_engines = 0.0 - self.inputs.fuel_to_air_ratio = 0.0 #changed + self.inputs.fuel_to_air_ratio = 0.0 self.outputs.thrust = 0.0 self.outputs.thrust_specific_fuel_consumption = 0.0 self.outputs.specific_impulse = 0.0 self.outputs.non_dimensional_thrust = 0.0 self.outputs.core_mass_flow_rate = 0.0 self.outputs.fuel_flow_rate = 0.0 - self.outputs.fuel_mass = 0.0 #changed + self.outputs.fuel_mass = 0.0 self.outputs.power = 0.0 self.design_thrust = 0.0 self.mass_flow_rate_design = 0.0 @@ -181,6 +181,7 @@ def compute(self,conditions): #Computing the TSFC TSFC = 3600.*f*g/(Fsp*a0*(1+bypass_ratio)) + #computing the core mass flow mdot_core = mdhc*np.sqrt(Tref/total_temperature_reference)*(total_pressure_reference/Pref) @@ -214,7 +215,8 @@ def compute_stream_thrust(self,conditions): Source: Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., "Hypersonic Airbreathing Propulsion", 1994 - + Chapter 4 - pgs. 175-180 + Inputs: conditions.freestream. isentropic_expansion_factor [-] @@ -305,7 +307,7 @@ def compute_stream_thrust(self,conditions): #fuel flow rate a = np.array([0.]) - fuel_flow_rate = np.fmax(FD2*TSFC/g,a) #use units package for the constants + fuel_flow_rate = np.fmax(FD2*TSFC/g,a) #computing the power power = FD2*u0 @@ -384,7 +386,8 @@ def size_stream_thrust(self,conditions): Source: Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., "Hypersonic Airbreathing Propulsion", 1994 - + Chapter 4 - pgs. 175-180 + Inputs: conditions.freestream.speed_of_sound [m/s] (conditions is also passed to self.compute(..)) self.inputs. diff --git a/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py b/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py index 50ca827287..916bf6efff 100644 --- a/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py +++ b/trunk/SUAVE/Methods/Aerodynamics/Common/Gas_Dynamics/Oblique_Shock.py @@ -81,8 +81,8 @@ def theta_beta_mach(M0,gamma,theta,n=0): """ # Calculate wave angle - MU = np.arcsin(1./M0) - c = np.tan(MU)*np.tan(MU) + mu = np.arcsin(1./M0) + c = np.tan(mu)*np.tan(mu) # Calculate shock angle a = ((gamma-1.)/2.+(gamma+1.)*c/2.)*np.tan(theta) From fb81c906de036a805c67ac5af1dcd04396dbe9e2 Mon Sep 17 00:00:00 2001 From: WalterMaier Date: Sun, 22 Apr 2018 17:08:30 -0700 Subject: [PATCH 5/6] github comments --- regression/scripts/AVL/avl_files/aircraft.avl | 2 +- regression/scripts/scramjet_network/scramjet_network.py | 2 +- 2 files changed, 2 insertions(+), 2 deletions(-) diff --git a/regression/scripts/AVL/avl_files/aircraft.avl b/regression/scripts/AVL/avl_files/aircraft.avl index 94aa467696..1e12f6fe03 100644 --- a/regression/scripts/AVL/avl_files/aircraft.avl +++ b/regression/scripts/AVL/avl_files/aircraft.avl @@ -62,7 +62,7 @@ SECTION SECTION #Xle Yle Zle Chord Ainc Nspanwise Sspace -32.4164746575 0.0 7.777 0.95 0.0 +32.4164746575 1.54 7.777 0.95 0.0 #--------------------------------------------------------- diff --git a/regression/scripts/scramjet_network/scramjet_network.py b/regression/scripts/scramjet_network/scramjet_network.py index d0673aec93..79379e0325 100644 --- a/regression/scripts/scramjet_network/scramjet_network.py +++ b/regression/scripts/scramjet_network/scramjet_network.py @@ -206,7 +206,7 @@ def energy_network(): scramjet.thrust = thrust #size the ramjet - scramjet_sizing(scramjet,6.5,20000.0) + scramjet_sizing(scramjet,size.mach_number,size.altitude) print "Design thrust :",scramjet.design_thrust print "Sealevel static thrust :",scramjet.sealevel_static_thrust From cf7783668b43a45190b5aa73681fe9778a3c9713 Mon Sep 17 00:00:00 2001 From: WalterMaier Date: Sun, 22 Apr 2018 17:15:17 -0700 Subject: [PATCH 6/6] missed comment --- trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py b/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py index 460b0bf155..3eda25fc94 100644 --- a/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py +++ b/trunk/SUAVE/Methods/Propulsion/scramjet_sizing.py @@ -54,7 +54,7 @@ def scramjet_sizing(scramjet,mach_number = None, altitude = None, delta_isa = 0, conditions.freestream.temperature = np.atleast_1d(T) conditions.freestream.density = np.atleast_1d(rho) conditions.freestream.dynamic_viscosity = np.atleast_1d(mu) - conditions.freestream.gravity = np.atleast_1d(9.81) + conditions.freestream.gravity = np.atleast_1d(SUAVE.Attributes.Planets.Earth().sea_level_gravity) conditions.freestream.isentropic_expansion_factor = np.atleast_1d(scramjet.working_fluid.compute_gamma(T,p)) conditions.freestream.Cp = np.atleast_1d(scramjet.working_fluid.compute_cp(T,p)) conditions.freestream.R = np.atleast_1d(scramjet.working_fluid.gas_specific_constant)