Hybrid propulsion concepts required development of nozzle system capable of withstanding gas temperatures in excess of 6200 F for burn times longer than 30 sec; tungsten nozzle insert systems provided best operation; heat transfer rates were lower with tungsten metal systems than for unmodified tungsten indicating that transpiration cooling was being realized; laboratory program subjecting infiltrated tungsten samples to plasma-arc heat source; technique offers excellent nozzle system for long time firing durations in hybrid and solid propellant rockets.


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    Title :

    Transpiration cooling with liquid metals


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 1 , n 1


    Publication date :

    1963


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    TRANSPIRATION COOLING WITH LIQUID METALS

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