A wind tunnel investigation has been conducted to determine the flow characteristics of the shock layer beneath the forebody of a hypersonic, airbreathing missile incorporating an aft-mounted inlet. In the inviscid part of the flow field, the measured parameters were in agreement with those predicted by a three-dimensional Method of Characteristics theory. At test conditions matching full scale Mach and Reynolds numbers at an altitude for maximum L/D cruise, boundary layer transition occurred downstream of the inlet face. While this means that a full size vehicle would have a more easily separated boundary layer, it is noted that the Reynolds number discrepancy between wind tunnel and actual flight conditions may result in a movement of the transition point to somewhere upstream of the inlet.


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    Titel :

    Mach 6 flow-field and boundary-layer surveys beneath the forebody of an airbreathing missile


    Beteiligte:
    Johnston, P. J. (Autor:in) / Hunt, J. L. (Autor:in)

    Erscheinungsdatum :

    01.01.1984


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Hypersonic Airbreathing Missile

    Hunt, J. L. / Lawing, P. L. / Marcum, D. C., Jr. | NTRS | 1978


    Hypersonic Airbreathing Missile

    J. L. Hunt / P. L. Lawing / D. C. Marcum | NTIS | 1978



    Forebody design for aerodynamic propulsion requirementsof an airbreathing hypersonic research vehicle

    Geetha, J. J. / Anavardham, T. K. G. / Panneerselvam, S. et al. | British Library Conference Proceedings | 2000