A model based on the fin effect for thermal condition of regeneratively cooled rocket engines is developed. The model uses the thermal resistance between hot-gas and coolant flow and implements a marching method along the coolant flow to determine the wall and coolant temperature and pressure distributions along the axial direction. The hot-gas flow and combustion is simulated using a CFD model for wall temperatures ranging from 540R to 1500R. The wall heat fluxes along axial direction are tabulated in a lookup table and an iterative procedure is used to evaluate the wall heat flux based on the wall temperature. Arrhenius equation is utilized to calculate chemical balance of reduced LH_2-LO_2 combustion process. It is shown that the result based on the fin analogy model is close to the data from previous published studies for the SSME. This study also discusses the effect of round corner of cooling channels on the heat transfer to the coolant flow. The results suggest that having curved corners have no effect on the thermal condition of the engine.
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