As design flight speeds are pushed progressively higher, the supersonic inlet becomes an increasingly important component of air-breathing propulsion systems. Currently, the turbojet engine is being considered for application at Mach numbers up to approximately 4 and the ramjet engine for application in the hypersonic region, or Mach numbers of 5 and above. Herein the inlet situation is surveyed and the merits of the various inlet-design philosophies are assessed on the basis of recent experimental data obtained at Mach numbers up to 5.


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    Titel :

    Inlets, exits, and cooling problems. 1 - Inlets


    Beteiligte:
    James F. Connors (Autor:in) / John L. Allen (Autor:in)


    Erscheinungsdatum :

    01.01.1957


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Inlets, exits, and cooling problems. 2 - Exits

    Englert, G. W. / Kochendorfer, F. D. | NTRS | 1957




    Design Criteria for Axisymmetric and Two-Dimensional Supersonic Inlets and Exits

    Connors, J.F. / Meyer, R.C. | Engineering Index Backfile | 1956