关键词: 固体火箭发动机;尾喷管;二维流;流伤;计算

Abstract: In this paper the flow field after grains in solid rocket engine is simulated and a simplified calculation model is assumed.By means of SIMPLE algorithm,a calculation analysis to the 2-D internal flow field with sudden shrink-after-sudden enlargement is also presented. In the calculation analysis, grid dividing, control volume selecting, treatment method of complex boundary condition, difference scheme selecting, equation discretization and solution of equations, etc.are analysed. The vortex pair obtained after the sudden enlargement stage coinsides with conclusion of Finaish, F. and Ghaddar, N.K. ,therefore Pan’s and Acrivos’s nested vortex group theory is further verified.

Key words: Solid rocket engine;Jet nozzle;Two-Dimensional flow;Flow field;Computation