Compressible Dynamic Stall Performance of a Variable Droop Leading Edge Airfoil with a Gurney Flap
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Authors
Chandrasekhara, M.S.
Martin, P.B.
Tung, C.
Subjects
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Date of Issue
2008-01
Date
January 2008
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Abstract
Results of a study using a passive approach to recover the loss of lift that occurred when a variable droop leading edge
(VDLE) airfoil was used to successfully control compressible dynamic stall by attach ing a small Gurney flap to it trailing edge are reported. Gurney flaps of' different heights were tested. The airfoil performance was evaluated by measuring the
unsteady pressures while it executed a sinusoidal pitch -Up maneuver over a range of Mach numbers from 0.2 to 0.4 at different reduced frequencies, with both static and dynamic leading edge droops. Not only was the " lost" lift recovered
completely with a 1 % chord-height Gurney flap, the drag and moment coefficients were also dramatically reduced and a
lift-to-drag ratio greater than 10 was achieved, making it an acceptable choice for this purpose. The improved performance is
explained through the basic fluid mechanics of the problem by discussing the various pressure distributions and the surface vorticity fluxes derived from these.
Type
Conference Paper
Description
(AIAA Paper No. 2004-0041), AHS Journal, Vol. 25, Jan. 2008, pp. 18-25.
Presented as AIAA Paper 2004-0041 at the Aerospace Sciences Meeting, Reno NV, January 2004
Presented as AIAA Paper 2004-0041 at the Aerospace Sciences Meeting, Reno NV, January 2004
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This study was supported by NASA Ames Research Center (monitored by T. Norman) and Army Aeroflightdynamics Directorate through a grant to the Naval Postgraduate School. Additional support for the VR12 airfoil studies was received from the Army Research Office (monitored by T. L. Doligalski)
Funding
MIPR3FNPSAR026
Format
Citation
M.S. Chandrasekhara, P.B. Martin and C. Tung, ﾓCompressible Dynamic Stall Performance of a Variable Droop Leading Edge Airfoil with a Gurney Flapﾔ, (AIAA Paper No. 2004-0041), AHS Journal, Vol. 25, Jan. 2008, pp. 1-6.
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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.