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.
M. G. Puopolo et al., "Comparison of Three Aerodynamic Models Used in Simulation of a High Angle of Attack UAV Perching Maneuver," Proceedings of the 51st AIAA Aerospace Sciences Meeting (2013, Grapevine, TX), American Institute of Aeronautics and Astronautics (AIAA), Jan 2013.
The definitive version is available at https://doi.org/10.2514/6.2013-242
51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 (2013: Jan. 7-10, Grapevine, TX)
Mechanical and Aerospace Engineering
Keywords and Phrases
Aerodynamic modeling; Aerodynamic models; Flat-plate theory; High angle of attack; Lift and drag coefficients; Oklahoma State University; Output parameters; Simulated flight, Aerospace engineering; Angle of attack, Computer simulation
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2013 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jan 2013