Gas-cycle nuclear-rocket power plants with hydrogen as propellant are considered as propulsion devices for space vehicles; summary of analysis conducted over range of reactor power of 46 to 1600 Mw; analysis of local heat-flux capability of coolant at nozzle throat indicated that cooling capability was inadequate to maintain wall temperature of 1440 R; techniques for improving capability such as h-p drop, high wall temperature, refractory wall coatings, etc.


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    Title :

    Analysis of nuclear-rocket nozzle cooling


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1960


    Size :

    24 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


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