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dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorCarr, L.W.
dc.contributor.authorWilder, M.C.
dc.date.accessioned2016-10-03T20:17:39Z
dc.date.available2016-10-03T20:17:39Z
dc.identifier.citationM.S.Chandrasekhara, L.W.Carr, and M.C.Wilder, モInterferometric Investigations of Compressible Dynamic Stall Over a Transiently Pitching Airfoilヤ, (AIAA Paper 93-0211), AIAA Journal, Vol. 32, No. 3, Mar. 1994, pp. 586-593.
dc.identifier.urihttp://hdl.handle.net/10945/50060
dc.description(AIAA Paper 93-0211), AIAA Journal, Vol. 32, No. 3, Mar. 1994, pp. 586-593.en_US
dc.descriptionThe article of record as published may be found at http://dx.doi.org/10.2514/3.12025
dc.description.abstractThe compressible dynamic stall flowfield over a NACA 0012 airfoil transiently pitching from 0 to 60 deg at a constant rate under compressible flow conditions has been studied using real-time interferometry. A quantitative description of the overall flowfield, including the finer details of dynamic stall vortex formation, growth, and the concomitant changes in the airfoil pressure distribution, has been provided by analyzing the interferograms. For Mach numbers above 0.4, small multiple shocks appear near the leading edge and are present through the initial stages of dynamic stall. Dynamic stall was found to occur coincidentally with the bursting of the separation bubble over the airfoil. Compressibility was found to confine the dynamic stall vortical structure closer to the airfoil surface. The measurements show that the peak suction pressure coefficient drops with increasing freestream Mach number, and also it lags the steady flow values at any given angle of attack. As the dynamic stall vortex is shed, an anti-clockwise vortex is induced near the trailing edge, which actively interacts with the post-stall flow.
dc.description.sponsorshipAir Force Office of Scientific Research Grant MIPR-92-0004
dc.description.sponsorshipArmy Research Office Grant MIPR-130-92
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.titleInterferometric Investigations of Compressible Dynamic Stall Over a Transiently Pitching Airfoilen_US
dc.typeArticleen_US
dc.description.funderAir Force Office of Scientific Research Grant MIPR-92-0004
dc.description.funderArmy Research Office Grant MIPR-130-92


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