--------------------------------------------- Run case 1: -unnamed- alpha -> CL = 0.390510 beta -> beta = 0.00000 pb/2V -> pb/2V = 0.00000 qc/2V -> qc/2V = 0.00000 rb/2V -> rb/2V = 0.00000 aileron -> Cl roll mom = 0.00000 elevator -> Cm pitchmom = 0.00000 rudder -> Cn yaw mom = 0.00000 alpha = -0.145500 deg beta = 0.00000 deg pb/2V = 0.00000 qc/2V = 0.00000 rb/2V = -0.282696E-35 CL = 0.390510 CDo = 0.835000E-02 bank = 0.00000 deg elevation = 0.00000 deg heading = 0.00000 deg Mach = 0.00000 velocity = 64.5396 ft/s density = 0.584600E-03 slug/ft^3 grav.acc. = 32.1800 ft/s^2 turn_rad. = 0.00000 ft load_fac. = 1.00000 X_cg = 0.246300E-01 Y_cg = 0.00000 Z_cg = 0.223900 mass = 0.177300 slug Ixx = 1.35000 slug-ft^2 Iyy = 0.750900 slug-ft^2 Izz = 2.09500 slug-ft^2 Ixy = 0.00000 slug-ft^2 Iyz = 0.00000 slug-ft^2 Izx = 0.00000 slug-ft^2 visc CL_a = 0.00000 visc CL_u = 0.00000 visc CM_a = 0.00000 visc CM_u = 0.00000