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A study of compressibility effects on dynamic stall of rapidly pitching airfoilsResults of recent experimental studies into the effect of compressibility on dynamic stall of oscillating airfoils are reviewed. Stroboscopic schlieren images of the strongly unsteady flow field are presented, showing the development of the dynamic stall vortex, and its progression down the airfoil. The effect of varying free-stream Mach number and frequency of oscillation of the airfoil are demonstrated, and examples of local supersonic flow are presented, including the presence of a shock near the leading edge of the airfoil.
Document ID
19950028594
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
External Source(s)
doi:10.1016/0010-4655(91)90155-E
Authors
Carr, Lawrence W. (NASA Ames Research Center Moffett Field, CA, United States)
Chandrasekhara, M. S. (NASA Joint Institute for Aeronautics, Monterey, CA United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1991
Publication Information
Publication: Computer Physics Communications
ISSN: 0010-4655
Subject Category
Aerodynamics
Accession Number
95A60193
Funding Number(s)
CONTRACT_GRANT: MIPR-AR0-137-86
CONTRACT_GRANT: AFOSR-MIPR-88-0010
Distribution Limits
Public
Copyright
Other

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