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dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorMartin, P.B.
dc.contributor.authorTung, C.
dc.dateJanuary 2008
dc.date.accessioned2016-10-05T15:52:06Z
dc.date.available2016-10-05T15:52:06Z
dc.date.issued2008-01
dc.identifier.citationM.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.
dc.identifier.urihttp://hdl.handle.net/10945/50147
dc.description(AIAA Paper No. 2004-0041), AHS Journal, Vol. 25, Jan. 2008, pp. 18-25.en_US
dc.descriptionPresented as AIAA Paper 2004-0041 at the Aerospace Sciences Meeting, Reno NV, January 2004
dc.description.abstractResults 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.
dc.description.sponsorshipThis 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)
dc.rightsThis 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.en_US
dc.titleCompressible Dynamic Stall Performance of a Variable Droop Leading Edge Airfoil with a Gurney Flapen_US
dc.typeConference Paperen_US
dc.description.funderMIPR3FNPSAR026


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