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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    Title :

    Transonic flow in unconventional nozzles


    Additional title:

    AIAA J


    Contributors:
    Hopkins, D.F. (author) / Hill, D.E. (author)

    Published in:

    AIAA Journal ; 6 , n 5


    Publication date :

    1968


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    Comment on Transonic Flow in Unconventional Nozzles

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


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    Two-zone transonic flow in nozzles.

    KLIEGEL, J. R. | AIAA | 1967