Nonlinear six-degree-of-freedom flight modeling of a high-wing cargo turboprop airplane was implemented using MATLAB. For the mathematical model, force and moment coefficient data were presented in look up tables as they were available from wind tunnel tests of 1/12 scale model of the airplane. Linear interpolations were used in evaluating aerodynamic data for angle of attack and sideslip angle and engine power for airspeed and altitude. Damping derivatives were obtained in subsonic range using empirical DATCOM methods. Programming routines for trim and numerical integration were included in this investigation. Time history variation of state variables shows aircraft motion at Mach 0.25, corresponding to a cruising altitude of 10,000 ft. The procedure described here should be useful for the preliminary dynamic modeling of the aircraft.
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