Show simple item record

dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorWilder, M.C.
dc.contributor.authorCarr, L.W.
dc.date.accessioned2016-10-03T20:17:34Z
dc.date.available2016-10-03T20:17:34Z
dc.identifier.citationM.S.Chandrasekhara, M.C. Wilder and L.W.Carr, モCompressible Dynamic Stall Control: Comparison of Two Approachesヤ, (Invited AIAA Paper 99-3122), Journal of Aircraft, Vol. 38, No. 3, pp. 448-453, May-Jun. 2001.
dc.identifier.urihttp://hdl.handle.net/10945/50046
dc.description(Invited AIAA Paper 99-3122), Journal of Aircraft, Vol. 38, No. 3, pp. 448-453, May-Jun. 2001.en_US
dc.description.abstractThe approaches of compressible dynamic stall control using real-time airfoil adaptation and slatted airfoils are compared. Each method attempts to solve the unsteady flow separation and the underlying causes differently. The approaches lead to unexpected results: For the slatted airfoil, dynamic stall alleviation on the main airfoil with a fully stalled slat occurred, and for the shape adapting airfoil, leading-edge attached flow with trailing-edge separation was obtained. In both cases, no dynamic stall vortex was present. As can be expected, the control effectiveness of each method varies over the full cycle and depends on the Mach number due to the new factors introduced by the use of the methods. These issues are addressed.
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 Control: Comparison of Two Approachesen_US
dc.typeArticleen_US
dc.description.funderU.S. Army Research Office, research grant MIPR8BNPSARO07


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record