A Discrete Vortex Method Application to High Angle of Attack Maneuvers

Document Type

Conference Paper

Publication Date


Publication Source

29th AIAA Applied Aerodynamics Conference


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.




Permission documentation is on file.


American Institute of Aeronautics and Astronautics

Place of Publication

Honolulu, HI