A review of experimental results from an ongoing study of the effects of compressibility on dynamic stall of an oscillating NACA 0012 airfoil is presented. The study shows that compressibility effects become significant at a free stream Mach number of 0.3. Dynamic stall is accelerated above this Mach number, but increasing unsteadiness delays onset of stall even under compressible flow conditions. Interferometric images of the flow show that process of dynamic stall occurs rapidly over a small angle of attack range. For certain flow conditions, multiple shocks form in the flow near the airfoil leading edge. The delay of stall has been shown to be due to delayed development combined with modification of the adverse pressure gradient in the flow Transition has been shown to significantly modify the observed flow behavior, and thus is a very important factor to be considered, especially since it occurs near the vortex formation location. Proper modelling of its effects is critical in dynamic stall flow computations.


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    Title :

    Compressibility effects on dynamic stall of oscillating airfoils


    Additional title:

    Kompressibilitäts- Auswirkungen auf einen Strömungsabriss bei schwingenden Tragflügeln


    Contributors:


    Publication date :

    1995


    Size :

    15 Seiten, 17 Bilder, 20 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Compressibility Effects on Dynamic Stall of Oscillating Airfoils

    Chandrasekhara, M. S. / Carr, L. W. / Advisory Group for Aerospace Research and Development et al. | British Library Conference Proceedings | 1995


    Dynamic stall experimenmts on oscillating airfoils

    McCroskey, W. / Carr, L. / McAlister, K. | Tema Archive | 1976


    Dynamic Stall Experiments on Oscillating Airfoils

    W.J. McCroskey / L.W. Carr / K.W. McAlister | AIAA | 1976


    Dynamic stall experiments on oscillating airfoils

    MCCROSKEY, W. / CARR, L. / MCALISTER, K. | AIAA | 1975