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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Passive control plate for shock-boundary layer interactions


    Beteiligte:

    Kongress:

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


    Erscheinungsdatum :

    01.01.1988


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Passive control plate for shock-boundary layer interactions

    GOODMAN, WESLEY / MORRISETTE, E. | AIAA | 1988



    Passive vortex control jets for shock boundary layer interactions

    Raghunathan, S. / O'Rourke, M. / Watterson, J. et al. | AIAA | 1999


    Passive Flow Control on Crossing Shock-Wave/Boundary-Layer Interactions

    Schwartz, Matthew J. / Stamper, Katherine / Bond, Ryan B. et al. | AIAA | 2019


    Shock-Wave/Boundary-Layer Interactions with Passive Blowing and Bleeding

    Lin, Y.-L. / Rimlinger, M. J. / Shih, T. I.-P. et al. | British Library Conference Proceedings | 1997