关键词: 喷管;跨音速流;流场;数值解;计算

Abstract: At present, the time dependent method has been widely used to predict transonic flow fields in solid rocket nozzles. The difference form of this method is explicit one which consumes excessive computational time because of the time steps limited by the stability criterion. Recently, the implicit form has been paid much attention. Beam, R.M.and Warming, R.F. presented an implicit approximation-factorization algorithm of Euler equation. Time steps longer than those requested in explicit form can be often taken.In this paper, the implicit approximation-factorization algorithm with the boundary-fitted coordinates system is applied to calculate steady inviscid transonic flows in nozzles. Three different nozzles which consist of throat with small curvature radius, steep convergent portion and submerged portion and therefore which parameters are changed seriously-are calculated. The good agreement of the computational results with experimental ones shows that the method is of good convergence and good accuracy. Due to the use of explicit form at the boundaries,Co-urant number is still limited to a certain degree, which is taken up to about 7 for the implicit procedure presented in this paper. This method can greatly accelerate the computation process and can be efficiently extended to tfae computations of N-S equation, PNS equation and viscid two-phase flow for solid rocket nozzles.

Key words: Nozzle;Transonic flow;Flow field;Numerical solution;Computation