Flow Visualization Studies of the Mach Number Effects on the Dynamic Stall of an Oscillating Airfoil

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dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorCarr, L.
dc.date.accessioned2016-10-03T17:55:26Z
dc.date.available2016-10-03T17:55:26Z
dc.date.issued1989-01
dc.description.abstractCompressibility effects on the dynamic stall of a NACA 0012 airfoil undergoing sinusoidal oscillatory motion were studied using a stroboscopic schlieren system. Schlieren pictures and some quantitative data derived from them are presented and show the influence of free-stream Mach number and reduced frequency on the dynamic-stall vortex. This study shows that a dynamic stall vortex always forms near the leading edge and convects on the airfoil upper surface at approximately 0.3 times the free stream velocity for all cases studied. The results also demonstrate that initiation of the the dynamic stall vortex is delayed to higher angles of attack with increased reduced frequency, but that dynamic stall occurs at lower angles of incidence with increasing Mach numbers.
dc.description.funderARO-MIPR-137-86
dc.description.funderAFOSR-MIPR-88
dc.description.funderNAVAIR
dc.identifier.citationM.S. Chandrasekhara and L. Carr, "Flow Visualization Studies of the Mach Number Effects on the Dynamic Stall of an Oscillating Airfoil", AIAA, 27th Aerospace Sciences Meeting, Reno, Nevada, January 9-12. 1989.
dc.identifier.otherAlAA 89-0023
dc.identifier.urihttps://hdl.handle.net/10945/50039
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.
dc.titleFlow Visualization Studies of the Mach Number Effects on the Dynamic Stall of an Oscillating Airfoilen_US
dc.typeConference Paper
dspace.entity.typePublication
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