Design and Development of a Dynamically Deforming Leading Edge Airfoil for Unsteady Flow Control
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Authors
Chandrasekhara, M.S.
Carr, L.W.
Wilder, M.C
Hiel, C.
Sticht, C.D.
Paulson, G.N.
Subjects
composit materials
stall control airfoil design
stall control airfoil design
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Abstract
A novel approach to unsteady flow separation and dynamic stall control using a dynamically deforming leading
edge airfoil is described. The design details of a carbon-fiber composite skin airfoil having a thickness of
0.002 in. at the leading edge and capable of deforming at 20 Hz in unsteady flow at freestream Mach numbers
of up to 0.45, are discussed. Implementation of the scheme at model scales places extraordinary demands on
the design, material and fabrication of such an airfoil. Rate scaling further requires very-rapid-response
instrumental ion, measurement techniques and data acquisition schemes. The special instrumentation control
system developed for these experiments as well as the fluid dynamic results of successful flow control that
was achieved using this method, are also discussed.
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Article
Description
ICIASF '97 RECORD, IEEE Publication No. 97CH36121, pp. 132-140.
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U.S. Army Research Office ARO MIPR 133-94, ARO 32480.11-EG
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U.S. Army Research Office ARO MIPR 133-94, ARO 32480.11-EG
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Citation
M.S.Chandrasekhara, L.W.Carr, M.C.Wilder, C.Hiel, C.D.Sticht, and G.N.Paulson, ﾓDesign and Development of a Dynamically Deforming Leading Edge Airfoil for Unsteady Flow Controlﾔ, ICIASFﾒ97 RECORD, IEEE Publication No. 97CH36121, pp. 132-140.
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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.