关键词: 火箭发动机喷管;紊流;边界层方程;对流传热

Abstract: on the basis of flowfield calculation, the Coupled control equations of turbulent boundany layer can be solved by using Patankar-Spalding integral-melhod with six-point scheme to obtain the heat exchange between the hot gas and nozzle wall. Couette flow analysis is to applied to the near wall region, and the slip value conception is applied the wall boundary and free boundary.Thus the relative accuracy of the calculation results is ensured. At last, the calculation results of this paper arc compared with the experimental data and the calculation results of Bartz formula.

Key words: Rocket nozzle;Turbulent flow;Boundary layer equation;Convection heat transfer