Comparison of Three Aerodynamic Models Used in Simulation of a High Angle of attack UAV Perching Maneuver

This investigation uses three aerodynamic models to simulate a pitch maneuver of a UAV system that is presently being developed at Oklahoma State University (OSU). The three aerodynamic models are relevant for high angle of attack flight, and they are based on methods that have been used in past research of UAV flight control. The first model assumes lift and drag coefficients are segmented linear functions of angle of attack. The second model is based on flat plate theory. The third model accounts for the transition between attached and separated flow. Output parameters of simulated flight maneuvers were compared, illustrating stark differences between the aerodynamic models. The magnitude of the differences emphasizes the critical need for accurate aerodynamic modeling when striving to predict motion of high angle of attack UAV maneuvers.