In an experiment using a single-degree-of-freedom (pitching) flutter model, which simulates the typical section of a forward-swept wing, shock-stall flutter, which is induced by large-scale shock-induced flow separation, has been observed by a schlieren system with a high-speed video camera. The experimental results are compared with computational ones to evaluate the numerical analysis code using the compressible Navier-Stokes equations. The mechanism of the shock-stall flutter is made clear by considering the relations between the pitching moments vs angle of attack and the flow patterns around the airfoil, which are obtained by the experimental flow visualization and the numerical simulation.


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    Title :

    Shock-stall flutter of a two-dimensional airfoil


    Additional title:

    Flattern eines zweidimensionalen Tragflügels infolge stoßwelleninduzierter Strömungsablösung


    Contributors:
    Yamasaki, M. (author) / Isogai, K. (author) / Uchida, T. (author) / Yukimura, It (author)

    Published in:

    AIAA Journal ; 42 , 2 ; 215-219


    Publication date :

    2004


    Size :

    5 Seiten, 7 Bilder, 5 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Shock Stall Flutter a Two-Dimensional Airfoil

    Yamasaki, M. / Uchida, T. / Yukimura, I. et al. | British Library Conference Proceedings | 2000


    Shock-Stall Flutter of a Two-Dimensional Airfoil

    Masahide Yamasaki / Koji Isogai / Takefumi Uchida et al. | AIAA | 2004


    Unsteady Airfoil Stall and Stall Flutter

    L. E. Ericsson / J. P. Reding | NTIS | 1971


    Unsteady airfoil stall and stall flutter

    Ericsson, L. E. / Reding, J. P. | NTRS | 1971