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.


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    Titel :

    Computational effects of inlet representation on powered hypersonic, airbreathing models


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    1993-10-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :





    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