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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:
    Singh, D. J. (Autor:in) / Tiwari, S. N. (Autor:in) / Kumar, A. (Autor:in)

    Kongress:

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


    Erscheinungsdatum :

    01.01.1989


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    3D Flow Computations Over Blunt Bodies at Hypersonic Speeds Using Shock-Fitting Technique

    Assonitis, Alessia / Paciorri, Renato / Gooch, Carl F. Ollivier et al. | TIBKAT | 2022


    3D flow computations over blunt bodies at hypersonic speeds using shock-fitting technique

    Assonitis, Alessia / Paciorri, Renato / Ollivier Gooch, Carl F. et al. | AIAA | 2022


    Hypersonic Type-IV Shock/Shock Interactions on a Blunt Body with Forward-Facing Cavity

    Xiao, Fengshou / Li, Zhufei / Zhu, Yujian et al. | AIAA | 2017

    Freier Zugriff