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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    Titel :

    Secondary gas injection in conical rocket nozzle


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Walker, R.E. (Autor:in) / Stone, A.R. (Autor:in) / Shandor, M. (Autor:in)

    Erschienen in:

    AIAA Journal ; 1 , n 2


    Erscheinungsdatum :

    1963


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    SECONDARY GAS INJECTION IN A CONICAL ROCKET NOZZLE

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



    Parametric Study of Secondary Gas Injection into a Conical Rocket Nozzle for Thrust Vectoring

    Erdem, Erinc / Albayrak, Kahraman / Tinaztepe, Tugrul | AIAA | 2006



    Parametric Study of Secondary Gas Injection into a Conical Rocket Nozzle for Thrust Vectoring

    Erdem, E. / Albayrak, K. / Tinaztepe, T. et al. | British Library Conference Proceedings | 2006