固体火箭发动机燃烧室喷管统一流场计算

采用ＳＩＭＰＬＥ算法的可压缩形式求解固体火箭发动机燃烧室喷管内的全速度统一流场;在非交错的配置网格基础上用有限体积法离散Ｎ－Ｓ方程,采用强隐式算法（ＳＩＰ）求解线性代数方程组;采用边界标志法实现复杂几何形状下的多区域统一计算;采用喷管外型逼近法保障计算稳定性;通过与同类计算结果的对比表明：上述算法的组合能够成功地获取固体火箭发动机内流场的整体结构。

Numerical Calculation of United Flow Field in SRM Chamber and Nozzle

United flow field at all flow speeds in the chamber and nozzle of SRM is solved by using the compressible form of the SIMPLE algorithm.The discrete N-S equations on the basis of the non-staggered collocated finite volume method and the strongly implicit procedure (SIP) are used to solve the linearized algebraic equation set.Moreover,multi-zone united calculation under complex geometry is realized by using boundary-marked method.The nozzle contour approximating is paid to assure stability of caluclation.The integrated structure of internal flow field of SRM can be obtained successfully by using the combination of these algorithms and the results can compare favorably with other numerical results.