A Study of Compressibility Effects on Dynamic Stall of Rapidly Pitching Airfoils
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Results of recent experimental studies into the effect of compressibility on dynamic stall of oscillating airfoils are reviewed. Stroboscopic schlieren images of the strongly unsteady flow field are presented, showing the development of the dynamic stall vortex, and its progression down the airfoil. The effect of varying free-stream Mach number, and frequency of oscillation of the airfoil are demonstrated, and examples of local supersonic flow are presented, including the presence of a shock near the leading edge of the airfoil.
Computer Physics Communications, Elsevier Science Publishers, B.V., Vol. 65(1991), pp. 62-68.
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