Unsteady Stall Control Using Dynamically Deforming Airfoils
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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.
The article of record as published may be found at http://dx.doi.org/10.2514/2.294
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