--------------------------------------------- Run case 1: -unnamed- alpha -> CL = 1.16647 beta -> beta = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.00000 rb/2V -> rb/2V = 0.00000 flap -> flap = 0.00000 aileron -> Cl roll mom = 0.00000 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 8.24035 beta = 0.00000 pb/2V = -0.645134E-24 qc/2V = 0.00000 rb/2V = -0.834026E-25 CL = 1.16647 CDo = 0.00000 bank = 0.00000 elevation = 0.00000 heading = 0.00000 Mach = 0.00000 velocity = 30.8633 density = 0.200000 grav.acc. = 10.0000 turn_rad. = 0.00000 load_fac. = 1.00000 X_cg = 0.650000 Y_cg = 0.00000 Z_cg = 0.00000 mass = 100.000 Ixx = 400.000 Iyy = 200.000 Izz = 600.000 Ixy = 0.00000 Iyz = 0.00000 Izx = 0.00000 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000 --------------------------------------------- Run case 2: -unnamed- alpha -> CL = 1.16647 beta -> beta = 5.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.00000 rb/2V -> rb/2V = 0.00000 flap -> flap = 0.00000 aileron -> Cl roll mom = 0.00000 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 8.30849 beta = 5.00000 pb/2V = 0.102044E-27 qc/2V = 0.00000 rb/2V = -0.921949E-26 CL = 1.16647 CDo = 0.00000 bank = 0.00000 elevation = 0.00000 heading = 0.00000 Mach = 0.00000 velocity = 30.8633 density = 0.200000 grav.acc. = 10.0000 turn_rad. = 0.00000 load_fac. = 1.00000 X_cg = 0.650000 Y_cg = 0.00000 Z_cg = 0.00000 mass = 100.000 Ixx = 400.000 Iyy = 200.000 Izz = 600.000 Ixy = 0.00000 Iyz = 0.00000 Izx = 0.00000 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000 --------------------------------------------- Run case 3: -unnamed- alpha -> CL = 1.16647 beta -> beta = 10.0000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.00000 rb/2V -> rb/2V = 0.00000 flap -> flap = 0.00000 aileron -> Cl roll mom = 0.00000 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 8.51450 beta = 10.0000 pb/2V = 0.775113E-25 qc/2V = 0.00000 rb/2V = -0.190600E-25 CL = 1.16647 CDo = 0.00000 bank = 0.00000 elevation = 0.00000 heading = 0.00000 Mach = 0.00000 velocity = 30.8633 density = 0.200000 grav.acc. = 10.0000 turn_rad. = 0.00000 load_fac. = 1.00000 X_cg = 0.650000 Y_cg = 0.00000 Z_cg = 0.00000 mass = 100.000 Ixx = 400.000 Iyy = 200.000 Izz = 600.000 Ixy = 0.00000 Iyz = 0.00000 Izx = 0.00000 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000 --------------------------------------------- Run case 4: -unnamed- alpha -> CL = 1.16647 beta -> beta = 15.0000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.00000 rb/2V -> rb/2V = 0.00000 flap -> flap = 0.00000 aileron -> Cl roll mom = 0.00000 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 8.86328 beta = 15.0000 pb/2V = -0.731872E-24 qc/2V = 0.00000 rb/2V = -0.271384E-24 CL = 1.16647 CDo = 0.00000 bank = 0.00000 elevation = 0.00000 heading = 0.00000 Mach = 0.00000 velocity = 30.8633 density = 0.200000 grav.acc. = 10.0000 turn_rad. = 0.00000 load_fac. = 1.00000 X_cg = 0.650000 Y_cg = 0.00000 Z_cg = 0.00000 mass = 100.000 Ixx = 400.000 Iyy = 200.000 Izz = 600.000 Ixy = 0.00000 Iyz = 0.00000 Izx = 0.00000 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000 --------------------------------------------- Run case 5: -unnamed- alpha -> CL = 1.16647 beta -> beta = 20.0000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.00000 rb/2V -> rb/2V = 0.00000 flap -> flap = 0.00000 aileron -> Cl roll mom = 0.00000 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 9.36338 beta = 20.0000 pb/2V = -0.172545E-23 qc/2V = 0.00000 rb/2V = -0.132873E-24 CL = 1.16647 CDo = 0.00000 bank = 0.00000 elevation = 0.00000 heading = 0.00000 Mach = 0.00000 velocity = 30.8633 density = 0.200000 grav.acc. = 10.0000 turn_rad. = 0.00000 load_fac. = 1.00000 X_cg = 0.650000 Y_cg = 0.00000 Z_cg = 0.00000 mass = 100.000 Ixx = 400.000 Iyy = 200.000 Izz = 600.000 Ixy = 0.00000 Iyz = 0.00000 Izx = 0.00000 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000