Computational and experimental results are presented for a passive method capable of reducing or completely eliminating the separation region in shock-boundary layer interactions of the type that can result in severe performance degradation due to flow separation in supersonic and hypersonic inlets. The method involves the placement of an embedded plate in the outer portion of the boundary layer, parallel to the wall, so that the incident shock will impinge upon, and be reflected from, its surface. This will lower the pressure gradient in the low-momentum, near-wall region. A porous control plate's effect has also been investigated.


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    Title :

    Passive control plate for shock-boundary layer interactions


    Contributors:

    Conference:

    AIAA, ASME, SIAM, and APS, National Fluid Dynamics Congress ; 1988 ; Cincinnati, OH, United States


    Publication date :

    1988-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Passive control plate for shock-boundary layer interactions

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