关键词: 喷管;跨音速流;粘性流;流场;计算

Abstract: In thispaper,having successfully computed inviscid transonic flow in nozzle using same method,we solve compressible laminar thin-layer N-S equations in conservation form adopting an implicit approximation-factorization algorithm in conjunction with generalized body-fitted coordinates.The parameters in core-flow, especially in boundary layer,are obtained through asymptotic solution of unsteady equations after suitable long time.The computed examples are the transonic viscous flow filed in two kinds of nozzle, one possesses rectangular section and the other axisymmetric.The agreement of computation results in comparison with measurements is very good for two kinds of nozzle. Many researchers adopted explicit algorithm,but we adopted implicit one.In our paper,CFL number may be taken to 150.Convergent speed is very quick and consequently the computer time using implicit algorithm in comparison with using explicit one is saved greatly. The comsumption of computer time may reduce to acceptable degree if the method presented in this paper is used to calculate viscous twe-phase rocket flow in nozzle.

Key words: Nozzle;Transoinc flow;Viscous flow;Flow field;Computation