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

Abstract

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.

Meeting Name

51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 (2013: Jan. 7-10, Grapevine, TX)

Department(s)

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)

978-162410181-6

Document Type

Article - Conference proceedings

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2013 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jan 2013

Link to Full Text

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