A theoretical analysis and numerical simulations are conducted to demonstrate the control capability of a splitter on the shock-wave/boundary-layer interactions in a generic hypersonic inlet with both a two-staged external compression and a strong cowl compression. The results show that, under the unstart condition, a well-designed splitter could suppress the massive cowl shock-induced separation, increase the fullness of the rampside boundary-layer profile at the isolator exit, and improve the inlet performance over the targeted operating Mach number range. With the splitter design, the severe shock-wave/boundary-layer interaction induced by the strong cowl shock is replaced by several weaker shock-wave/boundary-layer interactions with reduced shock intensity and boundary-layer thickness.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Control of Severe Shock-Wave/Boundary-Layer Interactions in Hypersonic Inlets


    Contributors:

    Published in:

    Publication date :

    2017-09-26


    Size :

    10 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Shock wave-boundary layer interactions in hypersonic inlets

    Watson, E. C. / Murphy, J. D. / Rose, W. C. | NTRS | 1967


    Manipulation of Shock/Boundary Layer Interactions in Hypersonic Inlets

    Schulte, D. / Henckels, A. / Neubacher, R. et al. | British Library Conference Proceedings | 1999


    Manipulation of Shock/Boundary-Layer Interactions in Hypersonic Inlets

    D. Schulte / A. Henckels / R. Neubacher | AIAA | 2001



    Control of Cowl Shock/Boundary-Layer Interaction in Hypersonic Inlets by Bump

    Zhang, Yue / Tan, Hui-jun / Sun, Shu et al. | AIAA | 2015