Hybrid flow control, a combination of micro-ramps and steady micro-jets, was experimentally investigated in the 15x15 cm Supersonic Wind Tunnel at the NASA Glenn Research Center. A central composite design of experiments method, was used to develop response surfaces for boundary-layer thickness and reversed-flow thickness, with factor variables of inter-ramp spacing, ramp height and chord length, and flow injection ratio. Boundary-layer measurements and wall static pressure data were used to understand flow separation characteristics. A limited number of profiles were measured in the corners of the tunnel to aid in understanding the three-dimensional characteristics of the flowfield.


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    Title :

    Effects of Hybrid Flow Control on a Normal Shock Boundary-Layer Interaction


    Contributors:

    Conference:

    AIAA Aerospace Sciences Meeting ; 2013 ; Grapevine, TX, United States


    Publication date :

    2013-01-07


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Effects of Hybrid Flow Control on a Normal Shock Boundary-Layer Interaction

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    Experimental Investigation of Normal Shock Boundary-Layer Interaction with Hybrid Flow Control

    Vyas, M. / Hirt, S. / Anderson, B. et al. | British Library Conference Proceedings | 2012