Analysis defining thrust effectiveness obtained by oxidizer injection into fuel-rich exhaust products in divergent section of nozzle; concept could be applied to liquid bipropellant system that yields stoichiometric temperature of reaction products too high to be tolerated in region of nozzle throat; stoichiometric temperature of reaction products could be attained in divergent section of nozzle where convective heating is less severe than at throat; results obtained from flow model indicate greater increase in nozzle thrust by oxidizer injection in nozzle exit cone than by same propellant mass addition in combustion chamber.


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    Titel :

    Thrust effectiveness of oxidizer injection in convergent-divergent nozzle


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Hall, G.R. (Autor:in)

    Erschienen in:

    AIAA Journal ; 2 , n 8


    Erscheinungsdatum :

    1964


    Format / Umfang :

    3 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



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