Term refers to liquid propellant engines used in ballistic missiles; basic unit is thrust chamber, in which pressure is maintained, and propulsive thrust produced, by continuous combustion of propellants; calculations show that of available propellant combinations, best performance is obtained with liquid oxygen and kerosene type fuel; thrust chamber heat transfer and combustion inefficiency; injector design; combustion instability and starting and control problems.


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    Title :

    Performance problems in large rocket engines


    Additional title:

    Roy Aeronautical Soc -- J


    Contributors:
    Bragg, S.L. (author)

    Published in:

    Publication date :

    1960


    Size :

    10 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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