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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    Title :

    Philosophy for improved rocket nozzle design


    Additional title:

    Jet Propulsion


    Contributors:

    Published in:

    Jet Propulsion ; 27 , n 10


    Publication date :

    1957


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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