Results of experiments performed at Johns Hopkins Univ on secondary gas injection into hot supersonic propellant flow in small rocket motor are presented; data on effects of injectant gas properties and injectant orifice size were obtained; motor operating conditions, nozzle geometry, and injectant location were kept fixed; main propellant was hot gas (catalytically decomposed 90% H2O 2), and motor conditions were held essentially constant.


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    Title :

    Secondary gas injection in conical rocket nozzle


    Additional title:

    AIAA J


    Contributors:
    Walker, R.E. (author) / Stone, A.R. (author) / Shandor, M. (author)

    Published in:

    AIAA Journal ; 1 , n 2


    Publication date :

    1963


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    SECONDARY GAS INJECTION IN A CONICAL ROCKET NOZZLE

    SHAND, A. J. / SHANDOR, M. / STONE, A. R. et al. | AIAA | 1963




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