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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    Title :

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


    Additional title:

    AIAA J


    Contributors:
    Howell, J.R. (author) / Strite, M.K. (author) / Renkel, H. (author)

    Published in:

    AIAA Journal ; 3 , n 4


    Publication date :

    1965


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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

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


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