Abstract: The viscous chemical reacting flow in nozzles was computed using a loosely coupled diagonal point implicit MacCormack scheme.This scheme solved the stiffness problem of governing equations and reduced the large scale work of inverting block matrices in normal point implicit schemes.The combustion process in the LH 2/LO 2 rocket engine was modeled using a 6 species and 8 step finite rate chemical reaction model,and the Baldwin Lomax algebraic turbulent model was adopted.The distributions of the flow parameters in nozzle were presented.The results show that the diagonal point implicit MacCormack scheme can improve computing efficiency greatly in computing the viscous chemical reacting flow in nozzles

Key words: Hydrogen oxygen engine;Nozzle flow;Reacting flow;Numerical calculation

摘要： 采用弱耦合对角化点隐式方法的ＭａｃＣｏｒｍａｃｋ格式，求解喷管的粘性化学反应流动，解决了控制方程组的刚性问题，又大大减少了常规点隐式方法中求逆矩阵的大量工作。对液氢液氧火箭发动机，采用６种组分、８个反应有限速率的化学反应模型和Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型，得到流场参数在喷管中的分布。计算结果表明，采用对角化点隐式方法求解化学反应喷管粘性流动能提高计算效率。

关键词: 氢氧发动机;喷管气流;反应流;数值计算;流体