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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    Titel :

    Transpiration cooling with liquid metals


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Robinson, A.T. (Autor:in) / McAlexander, R.L. (Autor:in) / Ramsdell, J.D. (Autor:in) / Wolfson, M.R. (Autor:in)

    Erschienen in:

    AIAA Journal ; 1 , n 1


    Erscheinungsdatum :

    1963


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    TRANSPIRATION COOLING WITH LIQUID METALS

    MC ALEXANDER / R. L. / RAMSDELL, J. D. et al. | AIAA | 1963


    Transpiration Cooling Using Liquid Water

    van Foreest, Arnold / Sippel, Martin / Gülhan, Ali et al. | AIAA | 2009


    Transpiration Cooling Using Liquid Water

    van Foreest, A. / Gulhan, A. / Esser, B. et al. | British Library Conference Proceedings | 2007


    Transpiration Cooling Using Liquid Water

    van Foreest, Arnold / Gülhan, Ali / Esser, Burkard et al. | AIAA | 2007


    Transpiration cooling panel

    DICHIARA ROBERT A JR | Europäisches Patentamt | 2023

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