A series of experiments have been conducted on a bleed hole array spanning the width of the Cambridge University Engineering Department supersonic wind tunnel at Mach numbers of 1.8 and 2.5. The wind tunnel was run with varying levels of suction, and the flow structure over the bleed array was subsequently mapped with a laser Doppler velocimetry system at a resolution of 0.25 hole diameters or better. The same wind-tunnel setup was simulated using the OVERFLOW Navier-Stokes equation solver. The information obtained was used primarily in qualitative comparisons of flow patterns. Overall good agreement was found in the definition of the expansion fan and barrier shock pattern produced by flow entering the normal holes, as well as three-dimensional flow patterns. Both studies agreed well in terms of measured mass flow rates, to within 1% of the boundary-layer mass flow. The presence of the barrier shock standing off the downstream edge of the bleed holes corresponded with a jet of upward flow, which may provide a mechanism for the generation of streamwise vortices. Presented as Paper 2014-2977 at the 32nd AIAA Applied Aerodynamics Conference, Atlanta, GA, 16-20 June 2014


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    Title :

    Experimental and Computational Investigations of a Normal-Hole-Bled Supersonic Boundary Layer



    Published in:

    AIAA journal ; 53 , 12


    Publication date :

    2015




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    50.93 / 55.50 Luftfahrzeugtechnik / 50.93 Weltraumforschung / 55.60 Raumfahrttechnik / 55.50 / 55.60
    Local classification TIB:    770/7040



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