A Study of Compressibility Effects on Dynamic Stall of Rapidly Pitching Airfoils

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Authors
Carr, L.W.
Chandrasekhara, M.S.
Subjects
dynamic stall
compressibility effects
unsteady flows
stroboscopic schlieren method
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Abstract
Results 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.
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Article
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Computer Physics Communications, Elsevier Science Publishers, B.V., Vol. 65(1991), pp. 62-68.
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https://hdl.handle.net/10945/50071
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U. S. Army Research Office, ARO 27894.4-EG
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U. S. Army Research Office, ARO 27894.4-EG
ARO MIPR 114-91
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Citation
L.W.Carr, and M.S.Chandrasekhara, ﾓA Study of Compressibility Effects on Dynamic Stall of Rapidly Pitching Airfoilsﾔ, Computer Physics Communications, Elsevier Science Publishers, B.V., Vol. 65 (1991), pp. 62-68.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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