--------------------------------------------- Run case 1: 0 deg. bank alpha -> CL = 0.700000 beta -> Cl roll mom = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.00000 rb/2V -> rb/2V = 0.00000 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 2.68832 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.885643E-26 CL = 0.700000 CDo = 0.170000E-01 bank = 0.00000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 5.64806 m/s density = 1.22500 kg/m^3 grav.acc. = 9.81000 m/s^2 turn_rad. = 0.00000 m load_fac. = 1.00000 X_cg = 3.40000 Y_cg = 0.00000 Z_cg = 0.500000 mass = 0.919500 kg Ixx = 0.205156 kg-m^2 Iyy = 0.775783E-01 kg-m^2 Izz = 0.279039 kg-m^2 Ixy = 0.00000 kg-m^2 Iyz = 0.00000 kg-m^2 Izx = -0.170174E-02 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: 10 deg. bank alpha -> CL = 0.700000 beta -> Cl roll mom = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.117765E-02 rb/2V -> rb/2V = 0.778743E-01 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 2.68832 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.885643E-26 CL = 0.700000 CDo = 0.170000E-01 bank = 10.0000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 5.69146 m/s density = 1.22500 kg/m^3 grav.acc. = 9.81000 m/s^2 turn_rad. = 18.7266 m load_fac. = 1.01543 X_cg = 3.40000 Y_cg = 0.00000 Z_cg = 0.500000 mass = 0.919500 kg Ixx = 0.205156 kg-m^2 Iyy = 0.775783E-01 kg-m^2 Izz = 0.279039 kg-m^2 Ixy = 0.00000 kg-m^2 Iyz = 0.00000 kg-m^2 Izx = -0.170174E-02 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: 20 deg. bank alpha -> CL = 0.700000 beta -> Cl roll mom = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.456854E-02 rb/2V -> rb/2V = 0.146356 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 2.68832 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.885643E-26 CL = 0.700000 CDo = 0.170000E-01 bank = 20.0000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 5.82648 m/s density = 1.22500 kg/m^3 grav.acc. = 9.81000 m/s^2 turn_rad. = 9.50775 m load_fac. = 1.06418 X_cg = 3.40000 Y_cg = 0.00000 Z_cg = 0.500000 mass = 0.919500 kg Ixx = 0.205156 kg-m^2 Iyy = 0.775783E-01 kg-m^2 Izz = 0.279039 kg-m^2 Ixy = 0.00000 kg-m^2 Iyz = 0.00000 kg-m^2 Izx = -0.170174E-02 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: 30 deg. bank alpha -> CL = 0.700000 beta -> Cl roll mom = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.976369E-02 rb/2V -> rb/2V = 0.197185 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 2.68832 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.885643E-26 CL = 0.700000 CDo = 0.170000E-01 bank = 30.0000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 6.06924 m/s density = 1.22500 kg/m^3 grav.acc. = 9.81000 m/s^2 turn_rad. = 6.50369 m load_fac. = 1.15470 X_cg = 3.40000 Y_cg = 0.00000 Z_cg = 0.500000 mass = 0.919500 kg Ixx = 0.205156 kg-m^2 Iyy = 0.775783E-01 kg-m^2 Izz = 0.279039 kg-m^2 Ixy = 0.00000 kg-m^2 Iyz = 0.00000 kg-m^2 Izx = -0.170174E-02 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: 40 deg. bank alpha -> CL = 0.700000 beta -> Cl roll mom = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.161365E-01 rb/2V -> rb/2V = 0.224230 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 2.68832 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.885643E-26 CL = 0.700000 CDo = 0.170000E-01 bank = 40.0000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 6.45316 m/s density = 1.22500 kg/m^3 grav.acc. = 9.81000 m/s^2 turn_rad. = 5.05897 m load_fac. = 1.30541 X_cg = 3.40000 Y_cg = 0.00000 Z_cg = 0.500000 mass = 0.919500 kg Ixx = 0.205156 kg-m^2 Iyy = 0.775783E-01 kg-m^2 Izz = 0.279039 kg-m^2 Ixy = 0.00000 kg-m^2 Iyz = 0.00000 kg-m^2 Izx = -0.170174E-02 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: 50 deg. bank alpha -> CL = 0.700000 beta -> Cl roll mom = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.229183E-01 rb/2V -> rb/2V = 0.224230 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 2.68832 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.885643E-26 CL = 0.700000 CDo = 0.170000E-01 bank = 50.0000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 7.04475 m/s density = 1.22500 kg/m^3 grav.acc. = 9.81000 m/s^2 turn_rad. = 4.24498 m load_fac. = 1.55572 X_cg = 3.40000 Y_cg = 0.00000 Z_cg = 0.500000 mass = 0.919500 kg Ixx = 0.205156 kg-m^2 Iyy = 0.775783E-01 kg-m^2 Izz = 0.279039 kg-m^2 Ixy = 0.00000 kg-m^2 Iyz = 0.00000 kg-m^2 Izx = -0.170174E-02 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 7: 60 deg. bank alpha -> CL = 0.700000 beta -> Cl roll mom = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.292911E-01 rb/2V -> rb/2V = 0.197185 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = 2.68832 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.885643E-26 CL = 0.700000 CDo = 0.170000E-01 bank = 60.0000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 7.98756 m/s density = 1.22500 kg/m^3 grav.acc. = 9.81000 m/s^2 turn_rad. = 3.75491 m load_fac. = 2.00000 X_cg = 3.40000 Y_cg = 0.00000 Z_cg = 0.500000 mass = 0.919500 kg Ixx = 0.205156 kg-m^2 Iyy = 0.775783E-01 kg-m^2 Izz = 0.279039 kg-m^2 Ixy = 0.00000 kg-m^2 Iyz = 0.00000 kg-m^2 Izx = -0.170174E-02 kg-m^2 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000