The effect of shock impingement on the blunt leading edge of the inlet cowl of a scramjet engine is investigated numerically. The impinging shock is caused by the vehicle forebody. The interaction of this forebody shock with the cowl leading edge shock results in a very complex flowfield containing local regions of high pressure and intense heating. In the present investigation, this complex flowfield is calculated by solving the full Navier-Stokes equations using a finite-volume flux splitting technique due to Van Leer. Results are also obtained for the downstream effects into the inlet of the leading edge shock-shock interactions. Results of the present numerical investigation are compared with available experimental results.


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    Title :

    Influence of shock-shock interactions on the blunt body flow field at hypersonic flight speeds


    Contributors:
    Singh, D. J. (author) / Tiwari, S. N. (author) / Kumar, A. (author)

    Conference:

    AIAA Applied Aerodynamics Conference ; 1989 ; Seattle, WA, United States


    Publication date :

    1989-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



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