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用偶合算法求解三维定常椭圆型Ｎ－Ｓ方程组，计算了火箭冲压发动机内部的湍流反应流场。用有限体积法离散控制方程，用块隐式法求解离散后的代数方程组。湍流流动用ｋ－ε模型描述，湍流燃烧采用掺混控制的局部瞬时不混合模型。实践表明，尽管密度场变化剧烈，仍能快速收敛。算例中网格点数为３９×１３×１８。计算出的燃烧效率符合实验结果。
The coupled algorithm was used to solve the three-dimensional steady elliptic N-S equations, and the turbulent flow field inside the rocket ramjet engine was calculated. The finite volume method is used to discretize the governing equations and the block implicit method to solve the discrete algebraic equations. Turbulent flow is described by a k-ε model and turbulent combustion is dominated by a locally mixed instantaneous non-mixing model. Practice shows that, despite the dramatic changes in the density field, rapid convergence can still occur. The number of grid points in the example is 39 × 13 × 18. The calculated combustion efficiency is consistent with the experimental results.