#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # Aircraft: # 1903 Wright Flyer # # File name: # wrightFlyer1903-nl-v1 # # ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # Author: # # Michael Selig # http://www.uiuc.edu/~m-selig # 2002/02/27 initial creation using # 2002/03/08 various refinements, focusing on the pitching moment behavior # #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # References: # # - Culick, F.E.C. and Jex, H.R., "Aerodynamics, Stability and # Control of the 1903 Wright Flyer," Proceedings of The Wright # Flyer: An Engineering Perspective, National Air and Space Museum, # Smithsonian Institution, 1985. # # - Jex, H.R. and Culick, F.E.C., "Flight Control Dynamics of the # 1903 Wright Flyer," 12th AIAA Atmospheric Flight Mechanics # Conference, AIAA Paper 85-1804-CP, 1985. # # - Jex, H, Grimm, R., Latz, J.P., and Hange, C., "Full-Scale 1903 # Wright Flyer Wind Tunnel Test Results From the NASA Ames Research # Center", AIAA 38th Aerospace Sciences Meeting, AIAA Paper # 2000-0512, 2000. # # - Various other sources including # http://www.wrightflyer.org/Papers/papers.html # http://amber.aae.uiuc.edu/~m-selig/uiuc_lsat.html (low Re data) # # - Additional models and updates # http://amber.aae.uiuc.edu/~m-selig/apasim.html # #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # # Notes: # - normal cruise speed: 30 mph # [] check rate derivatives # [x] check # [] simple engine used, check max thrust # [] apparent mass effects are not include #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ # aero forces are about a point 2 ft above the c.g. #init Dz_cg 0 # [ft] init use_V_rel_wind_2U init use_dyn_on_speed_curve1 init dyn_on_speed 2 init dyn_on_speed_zero 1 # geometry geometry bw 40.3 # [ft] geometry cbar 6.2 # [ft] # biplane! geometry Sw 518 # [ft^2] # canard controlSurface de 20 20 # [deg] # wing warping controlSurface da 12 12 # [deg] # rudder coupling: coupling wing warp to rudder is delta_r = 2.5 * delta_w # but code uses coupling of delta_r = delta_a/2, so here the max limits must be 1:5 controlSurface dr 60 60 # [deg] # if enable-auto-coordination is not used w/ FGFS startup options, then use # where 30 deg rudder can be used with 12 deg aileron (2.5:1) #controlSurface dr 30 30 # [deg] mass Weight 750 # [lb] # mass moments estimates from Culick paper mass I_xx 1318 # [slug-ft^2] mass I_yy 271 # [slug-ft^2] mass I_zz 1343 # [slug-ft^2] mass I_xz 0 # [slug-ft^2] # /* Wright Flyer # F_Z_aero += -(0.269 * Mass) * W_dot_body; # M_l_aero += -(0.59 * I_xx) * P_dot_body; # M_m_aero += -(0.14 * I_yy) * Q_dot_body; */ # Apparent mass terms mass Mass_appMass_ratio .269 mass I_xx_appMass_ratio .590 mass I_yy_appMass_ratio .14 # [] max thrust estimate engine simpleSingle 171 # [lb] # #engine simpleSingle 371 # [lb] # lift curve CL CLfade CLfade.dat 0 1 # drag polar CD CDfa CDfa.dat 0 1 # moment contributions Cm Cmfa Cmfa2.dat 0 1 Cm Cmfade Cmfade6.dat 0 1 1 Cm Cm_q -3.5 # [/rad], estimate # da negative right aileron TEU CY CY_beta -.321 # [/rad], -.0056/deg CY CY_da -.636 # [/rad], -.0111/deg CY CY_dr 0.241 # [/rad], 0.0042/deg # [] mss - update rate derivatives CY CY_p 0.0 # [/rad], placeholder CY CY_r 0.3 # [/rad], placeholder Cl Cl_beta 0.0212 # [/rad], 0.00037033/deg Cl Cl_da -0.1317 # [/rad], -.0023/deg Cl Cl_dr 0.007 # [/rad], 0.000125/deg # [] mss - update rate derivatives Cl Cl_p -0.5 # [/rad], placeholder Cl Cl_r 0 # [/rad], placeholder Cn Cn_beta 0.0335 # [/rad], 0.0005853/deg Cn Cn_dr -0.039 # [/rad], -.0069/deg Cn Cn_da 0.024 # [/rad], 0.000421/deg # [] mss - update rate derivatives Cn Cn_p -0.06 # [/rad], placeholder Cn Cn_r -0.15 # [/rad], placeholder # nose wheel (must be position 0 if present) gear Dx_gear 0 6.5 # x-offset from CG [ft] gear Dy_gear 0 0 # y-offset from CG [ft] gear Dz_gear 0 4.5 # z-offset from CG [ft] gear cgear 0 300 # damping [lbs/ft/sec] gear kgear 0 600 # springiness [lbs/ft] gear muGear 0 0 # 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 -8.5 # [ft] gear Dy_gear 1 3.25 # [ft] gear Dz_gear 1 4 # [ft] gear cgear 1 300 # [lbs/ft/sec] gear kgear 1 600 # [lbs/ft] gear muGear 1 0 # rolling coefficient gear strutLength 1 2.5 # gear travel [ft] (not yet used) # left gear (must be position 2 if present) gear Dx_gear 2 -8.5 # [ft] gear Dy_gear 2 -3.25 # [ft] gear Dz_gear 2 4 # [ft] gear cgear 2 300 # [lbs/ft/sec] gear kgear 2 600 # [lbs/ft] gear muGear 2 0 # rolling coefficient gear strutLength 2 2.5 # gear travel [ft] (not yet used) # right wing gear Dx_gear 3 0 # [ft] gear Dy_gear 3 21 # [ft] gear Dz_gear 3 1 # [ft] gear cgear 3 400 # [lbs/ft/sec] gear kgear 3 800 # [lbs/ft] gear muGear 3 0 # rolling coefficient gear strutLength 3 2.5 # gear travel [ft] (not yet used) # left wing gear Dx_gear 4 0 # [ft] gear Dy_gear 4 -21 # [ft] gear Dz_gear 4 1 # [ft] gear cgear 4 300 # [lbs/ft/sec] gear kgear 4 800 # [lbs/ft] gear muGear 4 0 # rolling coefficient gear strutLength 4 2.5 # gear travel [ft] (not yet used) #record elevator_deg #record Long_trim_deg #record Simtime #record Alpha_deg #record CL #record Cm #record elevator_deg #record aileron_deg #record rudder_deg #record CmfaI #record CmfadeI #record M_m_cg #record M_m_rp #record F_Z #record Dx_cg #record F_X #record Dz_cg *