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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Chandrasekhara, M.S.; Brydges, B.E. (1990-01);Amplitude effects on dynamic stall of an oscillating airfoil in locally transonic flow were studied using stroboscopic schlieren flow visualization. The dynamic stall vortex was photographed for various conditions and its ...
Beahan, James J.; Shih, Chiang; Krothapalli, Anjaneyulu; Kumar, Rajan; Chandrasekhara, Muguru S. (2014);Control of the dynamic stall process of a NACA 0015 airfoil undergoing periodic pitching motion is investigated experimentally at the NASA Ames compressible dynamic stall facility. Multiple microjet nozzles distributed ...
Chandrasekhara, M.S.; Platzer, M.F. (1990-08-23);A research proposal to investigate the "Compressibility Effects on Dynamic Stall of Oscillating Airfoils" was submitted to ARO and the project was funded in April 1986. The aim was to obtain a basic understanding of the ...