The present report discusses launcher flow-field data from complementary cold-gas test programs conducted at the University of Texas at Austin. Based on these data, flow-field models for the constrictive launcher configurations have been defined as a function of the nozzle-exit location and of the stagnation pressure in the nozzle reservoir. The conclusions are based on the configurations of the present experimental program.


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    Title :

    Experimental Study of an Underexpanded, Supersonic Nozzle Exhausting into a Constrictive Launch Tube


    Contributors:
    J. J. Bertin (author) / R. R. Morris (author) / G. M. Garms (author) / M. R. Motal (author) / H. T. Faria (author)

    Publication date :

    1975


    Size :

    61 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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