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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:

    Kongress:

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


    Erscheinungsdatum :

    07.01.2013


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



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

    Hirt, S. / Vyas, M. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2013


    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


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

    Vyas, Manan / Hirt, Stefanie / Anderson, Bernhard | AIAA | 2012