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dc.contributor.authorChandrasekhara, M.S.
dc.dateSeptember 1997
dc.date.accessioned2016-10-12T15:07:34Z
dc.date.available2016-10-12T15:07:34Z
dc.date.issued1997-09
dc.identifier.urihttp://hdl.handle.net/10945/50267
dc.description.abstractA three year research effort on "A Fundamental Study of Compressibility Effects on Dynamic Stall of Fixed and Adaptive Airfoils" was initiated in 1994. The research led to an understanding of: some of the key mechanisms of compressible dynamic stall including when the flow over the airfoil is transonic; the Reynolds number effects which strongly alter the detailed flow physics making extension of laboratory results to full-scale conditions extremely challenging, and the role of transition and a need to model it properly in computations. Further, the results demonstrated the major role of the airfoil leading edge curvature in producing the flow gradients that are responsible for dynamic stall onset, which enabled the development of a dynamically developing leading edge (DDLE) airfoil for effective flow control by modifying the vorticity field in the flow. The significant results of the effort are summarized in this report.en_US
dc.description.sponsorshipU.S. Army Research, ARO 32480.12-EGen_US
dc.format.extent46 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.titleA Fundamental Study of Compressibility Effects on Dynamic Stall of Fixed and Adaptive Airfoilsen_US
dc.typeReporten_US
dc.contributor.corporateNaval Postgraduate School (U.S.)en_US
dc.subject.authorcompressible dynamic stall mechanismsen_US
dc.subject.authorReynolds number effectsen_US
dc.subject.authoradaptive flows geometryen_US
dc.description.funderU.S. Army Research, ARO 32480.12-EGen_US
dc.description.funderARO-MIPR-133-94en_US


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