Several solutions for the internal flow in axisymmetric supersonic inlets at angle of attack were obtained. A shock-capturing finite-difference technique was used to obtain the solutions. Good overall agreement between the shock-capturing solutions and experimental data was obtained, except in regions of strong viscous effects or boundary-layer removal. The required centerbody translation with changes in freestream Mach number and angle of attack was obtained and agrees qualitatively with experimental data.


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    Titel :

    Internal flow calculations for axisymmetric supersonic inlets at angle of attack


    Beteiligte:
    Presley, L. L. (Autor:in)

    Kongress:

    Propulsion Conference ; 1975 ; Anaheim, CA


    Erscheinungsdatum :

    1975-09-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :