Goertler vortices arise in boundary layers along concave surfaces due to centrifugal effects. This paper presents some results of an experiment conducted to study the development of these vortices on an airfoil with a pressure gradient in the concave region where an attached laminar boundary layer was insured with suction through a perforated panel. The sublimating chemical technique was used to visualize Goertler vortices and the velocity field was measured by laser velocimetry. The vortex wavelength clearly varied with Goertler number as predicted by linear theory. Both flow visualization and velocity measurements indicated vortex damping in the convex zone. Secondary instability was observed at the higher Goertler numbers.


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    Titel :

    The Goertler Instability on an Airfoil


    Beteiligte:
    Mangalam, S. M. (Autor:in) / Dagenhart, J. R. (Autor:in) / Hepner, T. E. (Autor:in) / Meyers, J. F. (Autor:in)

    Kongress:

    AIAA 23rd Aerodynamic Sciences Meeting ; 1985 ; Reno, NV, United States


    Erscheinungsdatum :

    1985-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    The Goertler instability on an airfoil

    MANGALAM, S. / DAGENHART, J.R. / MEYERS, J. et al. | AIAA | 1985



    Goertler instability of wall jets

    FLORYAN, J. M. | AIAA | 1989


    Goertler instability on an airfoil: Comparison of marching solution with experimental observations

    Kalburgi, V. / Mangalam, S.M. / Degenhart, J.R. | Tema Archiv | 1989


    Secondary Goertler instability in hypersonic boundary layers

    Whang, Chong / Zhong, Xiaolin | AIAA | 2001