Compressible Dynamic Stall Control: Comparison of Two Approaches
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Authors
Chandrasekhara, M.S.
Wilder, M.C.
Carr, L.W.
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Abstract
The approaches of compressible dynamic stall control using real-time airfoil adaptation and slatted airfoils are
compared. Each method attempts to solve the unsteady flow separation and the underlying causes differently.
The approaches lead to unexpected results: For the slatted airfoil, dynamic stall alleviation on the main airfoil
with a fully stalled slat occurred, and for the shape adapting airfoil, leading-edge attached flow with trailing-edge
separation was obtained. In both cases, no dynamic stall vortex was present. As can be expected, the control
effectiveness of each method varies over the full cycle and depends on the Mach number due to the new factors
introduced by the use of the methods. These issues are addressed.
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(Invited AIAA Paper 99-3122), Journal of Aircraft, Vol. 38, No. 3, pp. 448-453, May-Jun. 2001.
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U.S. Army Research Office, research grant MIPR8BNPSARO07
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M.S.Chandrasekhara, M.C. Wilder and L.W.Carr, ﾓCompressible Dynamic Stall Control: Comparison of Two Approachesﾔ, (Invited AIAA Paper 99-3122), Journal of Aircraft, Vol. 38, No. 3, pp. 448-453, May-Jun. 2001.
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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.