--------------------------------------------- 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 = -0.622558E-01 deg beta = 0.295790E-14 deg pb/2V = -0.118080E-39 qc/2V = 0.00000 rb/2V = -0.137295E-39 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 = 3.50000 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: 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 = -0.170228 deg beta = -0.644007E-14 deg pb/2V = 0.155236E-31 qc/2V = 0.00000 rb/2V = -0.431921E-34 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 = 4.00000 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: 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 = -0.278206 deg beta = 0.309641E-14 deg pb/2V = -0.151468E-32 qc/2V = 0.00000 rb/2V = 0.109722E-34 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 = 4.50000 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: 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 = -0.386194 deg beta = 0.305308E-14 deg pb/2V = 0.295216E-32 qc/2V = 0.283286E-33 rb/2V = -0.329280E-34 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 = 5.00000 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: 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 = -0.494197 deg beta = 0.629389E-14 deg pb/2V = 0.00000 qc/2V = 0.338817E-29 rb/2V = 0.00000 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 = 5.50000 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: 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 = -0.602220 deg beta = 0.644984E-14 deg pb/2V = -0.347229E-33 qc/2V = 0.266904E-34 rb/2V = 0.390320E-41 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 = 6.00000 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: 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 = -0.710267 deg beta = 0.386854E-15 deg pb/2V = 0.243520E-37 qc/2V = 0.161746E-28 rb/2V = 0.130319E-40 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 = 6.50000 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