Description of compressible gas flow in throat region of rocket nozzles must be known to optimize wall contours and to predict performance; existence of subsonic and supersonic flow in close proximity does not permit use of conventional analytical techniques to obtain mathematical description of flow; analysis presented can treat annular flow passages that are either parallel to nozzle axis or inclined to it at some arbitrary angle; solution is not limited to nozzles with moderate wall radii of curvature; it is expected that solution will provide accurate starting conditions for method of characteristics to compute flowfield in supersonic region.


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    Titel :

    Transonic flow in unconventional nozzles


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Hopkins, D.F. (Autor:in) / Hill, D.E. (Autor:in)

    Erschienen in:

    AIAA Journal ; 6 , n 5


    Erscheinungsdatum :

    1968


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    Comment on Transonic Flow in Unconventional Nozzles

    D.B. MORDEN AND B.W. FARQUHAR | AIAA | 1969


    Transonic potential flow in hyperbolic nozzles

    Park, M. / Caughey, D. A. | NTRS | 1986


    Transonic potential flow in hyperbolic nozzles

    PARK, M. / CAUGHEY, D. A. | AIAA | 1986


    Two-zone transonic flow in nozzles.

    KLIEGEL, J. R. | AIAA | 1967