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dc.contributor.authorAhmed, S.
dc.contributor.authorChandrasekhara, M.S.
dc.dateSep 01, 1991en_US
dc.date.accessioned2018-09-27T00:06:21Z
dc.date.available2018-09-27T00:06:21Z
dc.date.issued1991-09
dc.identifier.other19910069250
dc.identifier.otherAIAA PAPER 91-3225
dc.identifier.urihttp://hdl.handle.net/10945/60071
dc.identifier.urihttps://ntrs.nasa.gov/search.jsp?R=19910069250
dc.descriptionApproved for public release, distribution unlimiteden_US
dc.description.abstractThe reattaching flow over an oscillating airfoil executing large amplitude sinusoidal motion around a mean angle of attack of 10 degrees has been studied using the techniques of stroboscopic schlieren, two component laser Doppler velocimetry and point diffraction interferometry, for a free stream Mach number of 0.3 and a reduced frequency of 0.05. The results show that the dynamically stalled flow reattaches in a process that begins when the airfoil is very close to the static stall angle on its downward stroke and progresses over the airfoil through a large range of angles of attack as the airfoil decreases to about 6 degrees. The airfoil suction peak shows a dramatic rise as the static stall angle is approached and the velocity profiles develop such that the flow near the surface is accelerated. The process completes through the disappearance of a separation bubble that forms over the airfoil.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.titleReattachment studies of an oscillating airfoil dynamic stall flow fielden_US
dc.typePreprint
dc.contributor.corporateAmes Research Center
dc.subject.authorAERODYNAMIC STALLINGen_US
dc.subject.authorAIRFOIL OSCILLATIONSen_US
dc.subject.authorFLOW DISTRIBUTIONen_US
dc.subject.authorREATTACHED FLOWen_US
dc.subject.authorWIND TUNNEL TESTSen_US
dc.subject.authorANGLE OF ATTACKen_US
dc.subject.authorBOUNDARY LAYER SEPARATIONen_US
dc.subject.authorFLOW VISUALIZATIONen_US
dc.subject.authorHYSTERESISen_US
dc.subject.authorROTARY WINGSen_US


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