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. Nomenclature
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