Unsteady Stall Control Using Dynamically Deforming Airfoils
| dc.contributor.author | Chandrasekhara, M.S. | |
| dc.contributor.author | Wilder, M.C. | |
| dc.contributor.author | Carr, L.W. | |
| dc.date.accessioned | 2016-10-03T20:17:47Z | |
| dc.date.available | 2016-10-03T20:17:47Z | |
| dc.description | The article of record as published may be found at http://dx.doi.org/10.2514/2.294 | en_US |
| dc.description.abstract | An 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.funder | ARO-MIPR-96-7 | |
| dc.description.funder | Air Force Office of Scientific Research | |
| dc.description.funder | S.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center | |
| dc.description.sponsorship | ARO-MIPR-96-7 | |
| dc.description.sponsorship | Air Force Office of Scientific Research | |
| dc.description.sponsorship | S.S. Davis, Fluid Mechanics Laboratory, NASA Ames Research Center | |
| dc.identifier.citation | M.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.uri | https://hdl.handle.net/10945/50069 | |
| dc.rights | This 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.title | Unsteady Stall Control Using Dynamically Deforming Airfoils | en_US |
| dc.type | Article | en_US |
| dspace.entity.type | Publication |
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