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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    Title :

    Thrust effectiveness of oxidizer injection in convergent-divergent nozzle


    Additional title:

    AIAA J


    Contributors:
    Hall, G.R. (author)

    Published in:

    AIAA Journal ; 2 , n 8


    Publication date :

    1964


    Size :

    3 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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