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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    Titel :

    Shock-stall flutter of a two-dimensional airfoil


    Weitere Titelangaben:

    Flattern eines zweidimensionalen Tragflügels infolge stoßwelleninduzierter Strömungsablösung


    Beteiligte:
    Yamasaki, M. (Autor:in) / Isogai, K. (Autor:in) / Uchida, T. (Autor:in) / Yukimura, It (Autor:in)

    Erschienen in:

    AIAA Journal ; 42 , 2 ; 215-219


    Erscheinungsdatum :

    2004


    Format / Umfang :

    5 Seiten, 7 Bilder, 5 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Shock-Stall Flutter of a Two-Dimensional Airfoil

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


    Unsteady airfoil stall and stall flutter

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


    Unsteady Airfoil Stall and Stall Flutter

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