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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    Title :

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


    Contributors:

    Conference:

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


    Publication date :

    1975-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    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


    Bleed System Design Technology for Supersonic Inlets

    Jan Syberg / Joseph L. Koncsek | AIAA | 1973