Experimental and Computational Analysis of High Angle of Attack Perching Maneuvers

Document Type

Conference Paper

Publication Date

6-2012

Publication Source

30th AIAA Applied Aerodynamics Conference

Abstract

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.

ISBN/ISSN

978-1-62410-185-4

Comments

Permission documentation is on file.

Publisher

American Institute of Aeronautics and Astronautics

Place of Publication

New Orleans, LA

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