Experimental and Computational Analysis of High Angle of Attack Perching Maneuvers
30th AIAA Applied Aerodynamics Conference
Experimental and numerical investigations are performed in an effort to elucidate the necessity of inclusion of three-dimensional effects in the determination of lift and drag forces during rapid pitching and impulsively started maneuvers to/at high angle of attack. Following the guidelines of the NATO RTO AVT 202 test case, wind tunnel data was acquired for pure pitching cases from 0 to 45 degrees for an AR 4 flat plate using the University of Dayton Low Speed Wind Tunnel (UD-LWST) and compared to a 2D Discrete Vortex Method (DVM).
Results show that the DVM compares well to the wind tunnel data in the pre-stall region before the deformation of the wake at the trailing edge by the trailing edge vortex and show similar trends in the post-stall region. It is believed that these differences in post-stall occur due to 3D effects and discussion is provided to support this assertion. The DVM is also used to compare results of a 45 degree linearly accelerated impulsive start case to data obtained in an experiment at the AFRL Horizontal Free-surface Water Tunnel under conditions identical to the simulation. Comparing these results again demonstrates the that DVM matches well to the water tunnel data except in a region where it is believed 3D instabilities are responsible for effects in the flowfield that are not adequately modeled by the 2D DVM.
Copyright © 2012, American Institute of Aeronautics and Astronautics
American Institute of Aeronautics and Astronautics
Place of Publication
New Orleans, LA
Lego, Zachary; Altman, Aaron; and Gunasekaran, Sidaard, "Experimental and Computational Analysis of High Angle of Attack Perching Maneuvers" (2012). Mechanical and Aerospace Engineering Faculty Publications. 112.