A Discrete Vortex Method for Application to MAV Perching
28th AIAA Applied Aerodynamics Conference
A code was developed in house to calculate the aerodynamics of a thin airfoil for low Reynolds number steady and unsteady aerodynamic applications using the Discrete Vortex Method. For validation, the code was tested by comparing the results to various steady and unsteady experimental and theoretical cases. It was found that the code approximated the theoretical circulation, lift, and wake shape results very well in every test case. In the future, the code will be used to approximate the Wagner function at high angles of attack, as well as investigate the effects of variable camber in high angle of attack maneuvers.
Copyright © 2010, American Institute of Aeronautics and Astronautics
American Institute of Aeronautics and Astronautics
Place of Publication
Hammer, Patrick; Altman, Aaron; and Eastep, Frank, "A Discrete Vortex Method for Application to MAV Perching" (2010). Mechanical and Aerospace Engineering Faculty Publications. 102.