Monte Carlo method is used as basis for determining two-dimensional propellant temperature distributions and wall heat-transfer rates as functions of axial position in nozzle of arbitrary shape; propellant is considered to be at such elevated temperatures that radiation is dominant mode of heat transfer, although effect of convection is also considered; propellant is assumed to be absorbing-emitting gas with constant absorption coefficient, and effects of flow, variable heat-transfer coefficient, propellant heat capacity, and nozzle wall temperature are included.


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    Titel :

    Heat-transfer analysis of rocket nozzles using very high temperature propellants


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Howell, J.R. (Autor:in) / Strite, M.K. (Autor:in) / Renkel, H. (Autor:in)

    Erschienen in:

    AIAA Journal ; 3 , n 4


    Erscheinungsdatum :

    1965


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Heat-transfer analysis of rocket nozzles using very high temperature propellants

    HOWELL, J. R. / RENKEL, H. / STRITE, M. K. | AIAA | 1965


    Uncooled Rocket Nozzles for Ultra-High Temperature Propellants

    Kraus, George | SAE Technical Papers | 1962



    RECOMBINATION LOSSES IN ROCKET NOZZLES WITH STORABLE PROPELLANTS

    KOPPANG, R. R. / SIMKIN, D. J. | AIAA | 1963


    Analysis of heat transfer in rocket nozzles

    Keizers, H. / Veraar, R. | AIAA | 1996