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dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorAhmed, S.
dc.contributor.authorCarr, L.W.
dc.dateAugust 20-22, 1990
dc.date.accessioned2016-11-02T01:22:22Z
dc.date.available2016-11-02T01:22:22Z
dc.date.issued1990-08
dc.identifier.citation8th Applied Aerodynamics Conference August 20-22, 1990/Portland,Oregonen_US
dc.identifier.urihttp://hdl.handle.net/10945/50450
dc.description.abstractCompressibility effects on the flowfield of an airfoil executing rapid transient pitching motion from 0 - 60 degrees over a wide range of Mach numbers and pitching rates were studied using a stroboscopic schlieren flow visualization technique. The studies have led to the first direct experiments] documentation of multiple shocks on the airfoil upper surface flow for certain conditions. Also, at low Mach numbers, additional coherent vortical structures were found to be present along with the dynamic stall vortex, whereas at higher Mach numbers, the flow was dominated by a single vortex. The delineating Mach number for significant compressibility effects was 0.3 and the dynamic stall process was accelerated by increasing the Mach number above that value. Increasing the pitch rate monotonically delayed stall to angles of attack as large as 27 degrees.en_US
dc.format.extent16 p.en_US
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.titleSchlieren Studies of Compressibility Effects on Dynamic Stall of Airfoils in Transient Pitching Motionen_US
dc.typeConference Paperen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)en_US
dc.description.funderAFOSR-MIPR-87-0029 and 88-0010en_US
dc.description.funderNAVAIRen_US
dc.description.funderAROen_US


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