An experimental investigation has been conducted to determine the effect of bleed region geometry and bleed rate on shock wave-boundary layer interactions in an axisymmetric, mixed-compression inlet at a Mach number of 2.5. The full realizable reduction in transformed form factor is obtained by bleeding off about half the incident boundary layer mass flow. Bleeding upstream or downstream of the shock-induced pressure rise is preferable to bleeding across the shock-induced pressure rise. Slanted holes are more effective than normal holes. Two different bleed hole sizes were tested without detectable difference in performance.


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    Titel :

    Control of shock-wave boundary-layer interactions by bleed in supersonic mixed compression inlets


    Beteiligte:
    Fukuda, M. K. (Autor:in) / Reshotko, E. (Autor:in) / Hingst, W. R. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference ; 1975 ; Anaheim, CA


    Erscheinungsdatum :

    01.09.1975


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Control of shock wave : boundary layer interactions by bleed in supersonic mixed compression inlets

    Fukuda, Michael K. / Hingst, Warren G. / Reshotko, Eli | TIBKAT | 1975



    Shock wave-boundary layer interactions in hypersonic inlets

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