Dynamic stall and unsteady boundary layer separation have been studied in incompressible flow at moderately large Reynolds numbers. By varying the leading-edge geometry of an NACA 0012 airfoil, three different types of stall were produced. For most of the configurations studied, including the basic NACA 0012 profile, dynamic stall was found not to originate with the bursting of a leading-edge laminar separation bubble, as is commonly believed. Instead, the vortex shedding phenomenon, which is the predominant feature of dynamic stall, appears to be fed its vorticity by the breakdown of the turbulent boundary layer.


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    Titel :

    Dynamic stall experiments on oscillating airfoils


    Beteiligte:
    Mccroskey, W. J. (Autor:in) / Carr, L. W. (Autor:in) / Mcalister, K. W. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1975 ; Pasadena, CA


    Erscheinungsdatum :

    01.01.1975


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Dynamic stall experiments on oscillating airfoils

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


    Dynamic Stall Experiments on Oscillating Airfoils

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


    Dynamic stall experimenmts on oscillating airfoils

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


    Compressibility effects on dynamic stall of oscillating airfoils

    Chandrasekhara, M.S. / Carr, L.W. | Tema Archiv | 1995


    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