Computational results are presented to illustrate the powered aftbody effects of representing the scramjet inlet on a generic hypersonic vehicle with a fairing, to divert the external flow, as compared to an operating flow-through scramjet inlet. This study is pertinent to the ground testing of hypersonic, airbreathing models employing scramjet exhaust flow simulation in typical small-scale hypersonic wind tunnels. The comparison of aftbody effects due to inlet representation is well-suited for computational study, since small model size typically precludes the ability to ingest flow into the inlet and perform exhaust simulation at the same time. Two-dimensional analysis indicates that, although flowfield differences exist for the two types of inlet representations, little, if any, difference in surface aftbody characteristics is caused by fairing over the inlet.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Computational effects of inlet representation on powered hypersonic, airbreathing models


    Contributors:

    Published in:

    Publication date :

    1993-10-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :





    Hypersonic Airbreathing Missile

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


    Hypersonic airbreathing propulsion

    Avery, W.H. / Dugger, G.L. | Engineering Index Backfile | 1964