A Discrete Vortex Method Application to High Angle of Attack Maneuvers

Author(s)

Patrick Hammer, Michigan State University
Aaron Altman, University of DaytonFollow
Frank Eastep, University of Dayton

Document Type

Conference Paper

Publication Date

6-2011

Publication Source

29th AIAA Applied Aerodynamics Conference

Abstract

A code implementing the Discrete Vortex Method was used to calculate the flowfield, pressures, lift coefficient, and drag coefficient on a flat plate pitching to high angles of attack, specifically 45 and 85 degrees. The method did a good job modeling the flow field around a flat plate pitching to the high angles of attack when compared to CFD and experimental results.

The code implemented the Uhlman method to capture vortex motion and surface effects so that the pressures around the airfoil could be calculated for the purposes of finding the lift and drag coefficients. The lift and drag coefficient results compared well with experimental and CFD results. Future use of the code will be to analyze a "perching" maneuver, in which the free stream velocity decreases to zero.

ISBN/ISSN

978-1-62410-145-8

Comments

Permission documentation is on file.

Copyright

Copyright © 2011, American Institute of Aeronautics and Astronautics

Publisher

American Institute of Aeronautics and Astronautics

Place of Publication

Honolulu, HI

eCommons Citation

Hammer, Patrick; Altman, Aaron; and Eastep, Frank, "A Discrete Vortex Method Application to High Angle of Attack Maneuvers" (2011). Mechanical and Aerospace Engineering Faculty Publications. 106.
https://ecommons.udayton.edu/mee_fac_pub/106