Unsteady Stall Control Using Dynamically Deforming Airfoils
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Authors
Chandrasekhara, M.S.
Wilder, M.C.
Carr, L.W.
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Abstract
An experiment documenting the compressible flow over a dynamically deforming airfoil is presented. This airfoil,
which has a leading-edge radius that can be dynamically changed, was tested at various deformation rates for fixed
airfoil angle of attack. Selected leading-edge shapes were also tested during airfoil oscillation. These tests show
that for a range of Mach numbers observed on the retreating blades of helicopter rotors the dynamic stall vortex
can be avoided by a judicious variation of leading-edge curvature.
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The article of record as published may be found at http://dx.doi.org/10.2514/2.294
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ARO-MIPR-96-7
Air Force Office of Scientific Research
S.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center
Air Force Office of Scientific Research
S.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center
Funder
ARO-MIPR-96-7
Air Force Office of Scientific Research
S.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center
Air Force Office of Scientific Research
S.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center
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M.S.Chandrasekhara, M.C.Wilder, and L.W.Carr, ﾓUnsteady Stall Control Using Dynamically Deforming Airfoilsﾔ, (AIAA Paper 97-2236), AIAA Journal, Vol. 36, No. 10, Oct. 1998, pp. 1792-1800.
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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.