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dc.contributor.authorChandrasekhara, M.S.
dc.date.accessioned2016-10-03T20:17:34Z
dc.date.available2016-10-03T20:17:34Z
dc.identifier.citationChandrasekhara, M.S., モCompressible Dynamic Stall Vorticity Flux Control Using a Dynamic Camber Airfoilヤ, Invited Paper Sadhana; Journal of Indian Academy of Sciences, Vol. 32, Part 1 & 2, FebruaryヨApril 2007, pp. 1ヨ10.
dc.identifier.urihttp://hdl.handle.net/10945/50045
dc.descriptionInvited Paper Sadhana; Journal of Indian Academy of Sciences, Vol. 32, Part 1 & 2, February-April 2007, pp. 1-10.en_US
dc.description.abstractThis study reports control of compressible dynamic stall through management of its unsteady vorticity using a variable droop leading edge (VDLE) airfoil. Through dynamic adaptation of the airfoil edge incidence, the formation of a dynamic stall vortex was virtually eliminated for Mach numbers of up to 0·4. Consequently, the leading edge vorticity flux was redistributed enabling retention of the dynamic lift. Of even greater importance was the fact that the drag and pitching moment coefficients were reduced by nearly 50%. The camber variations introduced when the leading edge was drooped are explained to be the source of this benefit. Analysis of the peak vorticity flux levels allowed the determination of minimum necessary airfoil adaptation schedule.
dc.description.sponsorshipUS ARO and AFDD
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 Vorticity Flux Control Using a Dynamic Camber Airfoilen_US
dc.typeArticleen_US
dc.subject.authorcompressible dynamic stall
dc.subject.authorunsteady vorticity control
dc.subject.authorcamber effects flow control
dc.description.funderUS ARO and AFDD


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