--------------------------------------------- Run case 1: -unnamed- alpha -> alpha = 0.00000 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 -> aileron = 0.00000 elevator -> elevator = 0.00000 rudder -> rudder = 0.00000 alpha = 0.00000 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = 0.00000 CL = 6.63067 CDo = 0.00000 bank = 0.00000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 0.00000 Lunit/Tunit density = 1.00000 Munit/Lunit^3 grav.acc. = 1.00000 Lunit/Tunit^2 turn_rad. = 0.00000 Lunit load_fac. = 0.00000 X_cg = 0.500000 Lunit Y_cg = 0.00000 Lunit Z_cg = 0.00000 Lunit mass = 1.00000 Munit Ixx = 1.00000 Munit-Lunit^2 Iyy = 1.00000 Munit-Lunit^2 Izz = 1.00000 Munit-Lunit^2 Ixy = 0.00000 Munit-Lunit^2 Iyz = 0.00000 Munit-Lunit^2 Izx = 0.00000 Munit-Lunit^2 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000