Schlieren Studies of Compressibility Effects on Dynamic Stall on Transiently Pitching Airfoils
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Authors
Chandrasekhara, M.S.
Ahmed, S.
Carr, L.W.
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Abstract
Compressibility effects on the flowfield of an airfoil executing rapid transient pitching motion from 0-60 deg
over a wide range of Mach numbers and pitching rates were studied using a stroboscopic schlieren flow
visualization technique. The studies have led to the first direct experimental documentation of multiple shocks
on the airfoil upper surface flow for certain conditions. Also, at low Mach numbers, additional coherent vortical
structures were found to be present along with the dynamic stall vortex, whereas at higher Mach numbers the
flow was dominated by a single vortex. The delineating Mach number for significant compressibility effects was
0.3 and the dynamic stall process was accelerated by increasing the Mach number above that value. Increasing
the pitch rate monotonically delayed stall to angles of attack as large as 27 deg.
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The article of record as published may be found at http://dx.doi.org/10.2514/3.48268
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AFOSR-MIPR-87-0029 and 88-0010
NAVAIR
ARO
NAVAIR
ARO
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AFOSR-MIPR-87-0029 and 88-0010
NAVAIR
ARO
NAVAIR
ARO
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M.S.Chandrasekhara, S. Ahmed, and L.W.Carr, ﾓSchlieren Studies of Compressibility Effects on Dynamic Stall on Transiently Pitching Airfoilsﾔ, (AIAA Paper 90-3038), Journal of Aircraft, Vol. 30, No. 2, Mar.-Apr., 1993, pp. 213-220.
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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.