Stability of a supersonic near-wall flow over a shallow grooved plate in the freestream of Mach 6 is investigated by means of numerical simulations and wind-tunnel experiments. Numerical solutions of two-dimensional Navier–Stokes equations are used to model propagation of artificial disturbances of several fixed frequencies generated by an actuator placed on the wall. It is shown that the high-frequency forcing excites unstable waves in the flat-plate boundary layer. These waves are relevant to the second-mode instability. The wavy wall damps the disturbances in a high-frequency band while it enhances them at lower frequencies. Stability experiments are conducted in the Institute of Theoretical and Applied Mechanics Tranzit-M shock tunnel under natural freestream conditions. The measured disturbance spectra are similar to those predicted numerically. They contain a peak associated with the second-mode instability. This peak is damped by the wavy wall, while a marginal increase of the disturbance amplitude is observed at lower frequencies. Although the experiments qualitatively confirm the wavy-wall stabilization concept, further stability and transition measurements are needed to clarify its robustness.


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    Titel :

    Stabilization of a Hypersonic Boundary Layer Using a Wavy Surface


    Beteiligte:
    Bountin, Dmitry (Autor:in) / Chimitov, Timur (Autor:in) / Maslov, Anatoly (Autor:in) / Novikov, Andrey (Autor:in) / Egorov, Ivan (Autor:in) / Fedorov, Alexander (Autor:in) / Utyuzhnikov, Sergey (Autor:in)

    Erschienen in:

    AIAA Journal ; 51 , 5 ; 1203-1210


    Erscheinungsdatum :

    01.05.2013




    Medientyp :

    Aufsatz (Konferenz) , Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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