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.
Heat-transfer analysis of rocket nozzles using very high temperature propellants
AIAA J
AIAA Journal ; 3 , n 4
1965
5 pages
Article (Journal)
English
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