The evolution of artificial disturbances in a laminar boundary layer on a flat plate model in the presence of an incident shock wave is considered. The flow is supersonic with the freestream Mach number M = 1.43. The results obtained in the two-dimensional computation are compared with the results obtained using the linear stability theory. The simulation is carried out in order to determine the possibility of using an electric discharge in the experiment as a source of first-mode disturbances. The discharge is simulated as a heat source. The results show a good agreement of two-dimensional computation with linear stability theory. It was demonstrated that discharge may be used as the source of first-mode disturbances.


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    Title :

    Evolution of artificial disturbances in separation area of laminar boundary layer for M = 1.43


    Contributors:

    Conference:

    INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2020) ; 2020 ; Novosibirsk, Russia


    Published in:

    Publication date :

    2021-05-24


    Size :

    6 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Laminar Boundary-Layer Response to Freestream Disturbances

    P.J. ERENS AND V.A.L. CHASTEAU | AIAA | 1974


    Nonlinear disturbances in a hypersonic laminar boundary layer

    KIMMEL, ROGER / KENDALL, JAMES | AIAA | 1991


    On laminar boundary-layer separation

    KLINEBERG, J. / STEGER, J. | AIAA | 1974



    INVESTIGATION OF 2D AND 3D BOUNDARY-LAYER DISTURBANCES FOR ACTIVE CONTROL OF LAMINAR SEPARATION BUBBLES

    Rist, K. A. U. / Wagner, S. / AIAA | British Library Conference Proceedings | 2003