Unsteady Stall Control Using Dynamically Deforming Airfoils

dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorWilder, M.C.
dc.contributor.authorCarr, L.W.
dc.date.accessioned2016-10-03T20:17:47Z
dc.date.available2016-10-03T20:17:47Z
dc.descriptionThe article of record as published may be found at http://dx.doi.org/10.2514/2.294en_US
dc.description.abstractAn experiment documenting the compressible flow over a dynamically deforming airfoil is presented. This airfoil, which has a leading-edge radius that can be dynamically changed, was tested at various deformation rates for fixed airfoil angle of attack. Selected leading-edge shapes were also tested during airfoil oscillation. These tests show that for a range of Mach numbers observed on the retreating blades of helicopter rotors the dynamic stall vortex can be avoided by a judicious variation of leading-edge curvature.
dc.description.funderARO-MIPR-96-7
dc.description.funderAir Force Office of Scientific Research
dc.description.funderS.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center
dc.description.sponsorshipARO-MIPR-96-7
dc.description.sponsorshipAir Force Office of Scientific Research
dc.description.sponsorshipS.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center
dc.identifier.citationM.S.Chandrasekhara, M.C.Wilder, and L.W.Carr, モUnsteady Stall Control Using Dynamically Deforming Airfoilsヤ, (AIAA Paper 97-2236), AIAA Journal, Vol. 36, No. 10, Oct. 1998, pp. 1792-1800.
dc.identifier.urihttps://hdl.handle.net/10945/50069
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.titleUnsteady Stall Control Using Dynamically Deforming Airfoilsen_US
dc.typeArticleen_US
dspace.entity.typePublication
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