#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # Aircraft: # Sopwith F.1 Camel # # File name: # sopwithCamel-v1-nl # # ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # Authors: # # Michael Selig # http://www.uiuc.edu/~m-selig # #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # Notes: # 2002/09/21 Initial development # 2002/09/11 Several refinements since initial work. # #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # References: # #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # Specs: # Stall speed = ~48 knots # Max speed = 102.5 knots w/ Bentley 150 Hp engine (118 mph) # Max rate of climb at sea level = 1100 fpm # Weight = 1430 lb w/ half fuel in main tank # #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # Todo items # [] add in torque (gyroscopic forces are model already) # [] placeholder data below # [] model spin by including nonlinear cn data #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # various "init" FGFS settings init use_V_rel_wind_2U init use_dyn_on_speed_curve1 init dyn_on_speed 2 init dyn_on_speed_zero 1 init use_Alpha_dot_on_speed 7 # [ft/sec] speed below which Alpha_dot is set to zero init downwashMode 100 init downwashCoef 0.030 # [1/ft] [x] Sopwith Camel notes 020928 p 1 # geometry data geometry bw 28. # [ft] [x] Sopwith Camel notes 020921 p 1 geometry cbar 8.25 # [ft] [x] geometry Sw 231. # [ft^2] [x] # control deflections controlSurface de 16.5 13.4 # [deg] [x] 16.5 nose up, 13.4 nose down controlSurface da 14 14 # [deg] [x] controlSurface dr 20.2 20.2 # [deg] [x] mass Weight 1430 # [lb] [x] see Sopwith Camel notes 020921 p 2, flying w/ 1/2 main tank full mass I_xx 727.7 # [slug-ft^2] [x] calculated from weights and balance data (see spreadsheet) mass I_yy 595.6 # [slug-ft^2] [x] calculated from weights and balance data (see spreadsheet) mass I_zz 1137.42 # [slug-ft^2] [x] calculated from weights and balance data (see spreadsheet) mass I_xz 0 # [slug-ft^2] [x] calculated from weights and balance data (see spreadsheet) # Apparent mass terms mass Mass_appMass_ratio .0868 # [x] apparent mass notes 020927 p 1 mass I_xx_appMass_ratio .12 # [x] apparent mass notes 020927 p 1 mass I_yy_appMass_ratio .034 # [x] apparent mass notes 020927 p 1 engine simpleSingleModel 450 -5 290 # [lb] [fps] [lb/fps] # where token3 - static thrust in [lb] # token4 - speed at which thrust goes to zero [ft/sec] # token5 - slope dT/dV at the speed at which thrust goes to zero [lb/fps] # turn on gyroscopic forces between pitch/yaw and engine rotation engine gyroForce_Q_body engine gyroForce_R_body engine omegaRPM 300 1250 # [rpm] {minOmegaRPM} {maxOmegaRPM} #engine omega {minOmega} {maxOmega} #engine polarInertia 24.4019 # [slug-ft^2] engine polarInertia 19.2143 # [slug-ft^2] engine slipstream_effects engine propDia 9.33 # [ft] [x] 020921 p 2 spreadsheet # [] need to write code for these two lines and turn on #engine eta_q_CL_adot 1 #engine eta_q_CL_q 1 engine eta_q_Cm_q 1 engine eta_q_Cm_adot 1 engine eta_q_Cmfade 1 #engine eta_q_Cl_beta 1 #engine eta_q_Cl_p 1 #engine eta_q_Cl_r 1 engine eta_q_Cl_dr 1 engine eta_q_CY_beta 1 #engine eta_q_CY_p 1 #engine eta_q_CY_r 1 engine eta_q_CY_dr 1 engine eta_q_Cn_beta 1 engine eta_q_Cn_p 1 engine eta_q_Cn_r 1 engine eta_q_Cn_dr 1 # Lift buildup # Lift curve CL CLfa CLfa.dat 0 1 # [x] Sopwith Camel notes p 020927 p 4 CL CL_adot 0.5776 # [/rad] [x] Sopwith Camel notes 020928 p 3 CL CL_q 1.153 # [/rad] [x] Sopwith Camel notes 020928 p 4 # drag build up # aircraft parasite drag CD CDo 0.0378 # [x] NASA SP-468 # extra wing parasite drag CD CDfa CDfa.dat 0 1 1 # [x] Sopwith Camel notes p 020927 p 4 # drag due to elevator deflection CD CD_de 0.007 # [x] Sopwith Camel notes 021018 p 2 #CD CDfade CDfade.dat 0 1 1 # - induced drag CD CDK 0.0645 # [x] Sopwith Camel notes 020928 p 1 # Pitching moment # Moment due to wing from nominally +-180 deg Cm Cmfa Cmfa.dat 0 1 # [x] Sopwith Camel notes p 020927 p 4 # Moment due to tail curve from nominally +-180 deg Cm Cmfade Cmfade.dat 0 1 1 # [x] Sopwith Camel notes 021019 p 2 Cm Cm_adot -0.9612 # [/rad] [x] Sopwith Camel notes 020928 p 3 Cm Cm_q -1.9182 # [/rad] [x] Sopwith Camel notes 020928 p 4 # due to side slip CY CY_beta -0.419 # [/rad] [x] Sopwith Camel 021017 p 4 Cl Cl_beta -0.01 # [/rad] [] placeholder Cn Cn_beta 0.105 # [/rad] [x] Sopwith Camel notes 021017 p 1 # due to aileron deflection #CY CY_da 0 Cl Cl_da -0.168 # [/rad] [x] Sopwith Camel notes 021016 p 2 Cn Cn_da 0.028 # [/rad] [x] S&C notes 021016 p 3 # due to rudder deflection CY CY_dr 0.041 # [/rad] [x] Sopwith Camel notes 021016 p 5 Cn Cn_dr -0.030 # [/rad] [x] Sopwith Camel notes 021016 p 6 Cl Cl_dr 0.0023 # [/rad] [x] Sopwith Camel notes 021016 p 6 # due to roll rate CY CY_p -0.004 # [/rad] [x] S&C notes 021016 p 5 Cl Cl_p -0.289 # [/rad] [x] Sopwith Camel notes 021016 p 1 Cn Cn_p -0.0286 # [/rad] [x] S&C notes 021016 p 4 # due to yaw rate CY CY_r 0.1218 # [/rad] [x] Sopwith Camel 021017 p 6 Cl Cl_r 0.100 # [/rad] [x] S&C notes 021018 p 1 Cn Cn_r -0.0788 # [/rad] [x] S&C notes 021018 p 1 and Sopwith Camel 021017 p 5 # nose wheel (must be position 0 if present) gear Dx_gear 0 25.5 # x-offset from CG [ft] gear Dy_gear 0 0 # y-offset from CG [ft] gear Dz_gear 0 -0.5 # z-offset from CG [ft] gear cgear 0 100 # damping [lbs/ft/sec] gear kgear 0 200 # springiness [lbs/ft] gear muGear 0 0.01 # rolling coefficient gear strutLength 0 -0.5 # gear travel [ft] (not yet used) # right gear (must be position 1 if present) gear Dx_gear 1 0.444 # [ft] gear Dy_gear 1 2.16 # [ft] gear Dz_gear 1 5.1 # [ft] gear cgear 1 600 # [lbs/ft/sec] gear kgear 1 1200 # [lbs/ft] gear muGear 1 0.01 # rolling coefficient gear strutLength 1 2.5 # [ft] # left gear (must be position 2 if present) gear Dx_gear 2 0.444 # [ft] gear Dy_gear 2 -2.16 # [ft] gear Dz_gear 2 5.1 # [ft] gear cgear 2 600 # [lbs/ft/sec] gear kgear 2 1200 # [lbs/ft] gear muGear 2 0.01 # rolling coefficient gear strutLength 2 2.5 # [ft] # tail dragger gear Dx_gear 3 -12.79 # [ft] gear Dy_gear 3 0 # [ft] gear Dz_gear 3 1.4 # [ft] gear cgear 3 100 # [lbs/ft/sec] gear kgear 3 200 # [lbs/ft] gear muGear 3 0.05 # rolling coefficient gear strutLength 3 2.5 # [ft] # left wing tip gear Dx_gear 4 1.356 # [ft] gear Dy_gear 4 -14.0 # [ft] gear Dz_gear 4 2.2 # [ft] gear cgear 4 150 # [lbs/ft/sec] gear kgear 4 300 # [lbs/ft] gear muGear 4 10.0 # rolling coefficient gear strutLength 4 2.5 # [ft] # right wing tip gear Dx_gear 5 1.356 # [ft] gear Dy_gear 5 14.0 # [ft] gear Dz_gear 5 2.2 # [ft] gear cgear 5 150 # [lbs/ft/sec] gear kgear 5 300 # [lbs/ft] gear muGear 5 10.0 # rolling coefficient gear strutLength 5 2.5 # [ft] * record Simtime record Alpha_deg record Beta_deg record CL record CLfaI record CD record CDfaI record Cm record CmfaI * record V_rel_wind record Simtime #record Alpha_deg record Beta_deg * # various record lines below are perserved for future development * #record debug2 * #record CmfadeI #record debug1 #record F_X_engine #record F_X_aero #record Alpha_deg #record debug2 #record debug3 #record V_rel_wind #record Beta_deg * #record CL #record elevator_deg * #record eta_q #record Q_body #record R_body #record Throttle_3 #record debug1 #record debug2 #record debug3 * #record V_rel_wind #record F_Z_aero #record Dynamic_pressure #record CL #record CLfaI #record CL_adot_save #record CL_q_save #record Alpha_dot * #record Throttle_3 #record V_calibrated_kts #record F_X_engine #record Alpha_deg #record CmfaI #record Cm * #record Simtime #record rudder #record aileron #record Alpha #record CDfaI #record CLfaI #record CmfaI #record CDfadeI #record CLfadeI #record aileron #record ClfadaI #record CnfadaI #record Beta #record rudder #record CYfbetadrI #record CnfbetadrI *