A large-scale low-boom inlet concept was tested in the NASA Glenn Research Center 8- x 6- foot Supersonic Wind Tunnel. The purpose of this test was to assess inlet performance, stability and operability at various Mach numbers and angles of attack. During this effort, two models were tested: a dual stream inlet designed to mimic potential aircraft flight hardware integrating a high-flow bypass stream; and a single stream inlet designed to study a configuration with a zero-degree external cowl angle and to permit surface visualization of the vortex generator flow on the internal centerbody surface. During the course of the test, the low-boom inlet concept was demonstrated to have high recovery, excellent buzz margin, and high operability. This paper will provide an overview of the setup, show a brief comparison of the dual stream and single stream inlet results, and examine the dual stream inlet characteristics.


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    Titel :

    Experimental Investigation of a Large-Scale Low-Boom Inlet Concept


    Beteiligte:

    Kongress:

    29th AIAA Applied Aerodynamics Conference ; 2011 ; Honolulu, HI, United States


    Erscheinungsdatum :

    27.06.2011


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Experimental Investigation of a Large-Scale Low-Boom Inlet Concept (Invited)

    Hirt, S. / Chima, R. / Vyas, M. et al. | British Library Conference Proceedings | 2011


    Experimental Investigation of a Large-Scale Low-Boom Inlet Concept (Invited)

    Hirt, Stefanie / Chima, Rodrick / Vyas, Manan et al. | AIAA | 2011



    Large-Scale Low-Boom Inlet Test Overview

    Hirt, Stefanie | NTRS | 2011


    Surface Flow and PSP Measurements in the Large-Scale Low-Boom Inlet (Invited)

    Herges, T. / Dutton, J. / Elliott, G. et al. | British Library Conference Proceedings | 2011