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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    Title :

    Internal flow calculations for axisymmetric supersonic inlets at angle of attack


    Contributors:

    Conference:

    Propulsion Conference ; 1975 ; Anaheim, CA


    Publication date :

    1975-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :