3-dimensional analysis of supersonic contoured nozzles; study undertaken in order to arrive at design of short, axially symmetric nozzles having axially directed exhaust and either, or both, improved performance and less weight than conventional conical nozzles; procedure for applying characteristic method of flow analysis in nozzle in arriving at proper nozzle wall contour for axial exhaust.


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    Titel :

    Philosophy for improved rocket nozzle design


    Weitere Titelangaben:

    Jet Propulsion


    Beteiligte:
    Dillaway, R.B. (Autor:in)

    Erschienen in:

    Jet Propulsion ; 27 , n 10


    Erscheinungsdatum :

    1957


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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