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发展了一种在任意曲线坐标系上求解湍流Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程的数值方法，采用了雷诺时均方程、Ｋ－ε两方程模型，并使用壁面函数法处理近壁区，在准定常假设下，计算了固体火箭发动机燃烧室内的二维轴对称不可压流场．该算法以ＳＩＭＰＬＥ为基础，但计算是在非交错网络上进行的．计算结果表明：二维计算与传统的一维计算相比，能较全面地反映出通道内各参数的分布，并能反映出通道发生变化所引起的流场变化．湍流与层流计算相比各参数的分布有一定差别．
A numerical method for solving turbulent Navier-Stokes equations on arbitrary curvilinear coordinate system is developed. Reynolds averaged equations and K-ε two-equation models are developed and the wall function method is used to deal with the near wall region. Under the quasi-stationary assumption, The two-dimensional axisymmetric incompressible flow field in a solid rocket motor combustion chamber was calculated. The algorithm is based on SIMPLE, but calculations are performed on non-interlaced networks. The calculation results show that compared with the traditional one-dimensional calculation, two-dimensional calculation can more fully reflect the distribution of each parameter in the channel and reflect the change of flow field caused by the channel change. Turbulence and laminar flow compared to the distribution of the parameters have some differences.