At flight speeds above about Mach 2 cross-sectional area of fully-expanded jet nozzle tends to be larger than intake streamtube; principle of integrating this increase in area of propulsion unit with usable volume to reduce after-body drag of combination is discussed and calculations are made to establish order of effect; it is deduced that successful integration of this type can produce worthwhile increases in lift/drag ratio; pertinence to air-breathing engines.


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    Titel :

    Use of excess engine exit area over intake area to reduce zero-lift drag at high supersonic speeds


    Weitere Titelangaben:

    Aeronautical Qarterly


    Beteiligte:
    Squire, L.C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1965


    Format / Umfang :

    15 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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