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从N－S方程出发，采用先进的矢通量分裂算法，对亚跨超音速喷管内流场进行了整体模拟计算。文中对几种不同计算格式的计算效率进行了比较，给出了超音速占优混合流动的直接分割求解方法。计算采用代数湍流模型，跨音速段的计算结果同其它实验和计算结果进行了比较。计算中发现对出口边界条件进行亚音速、超音速和有回流分别处理很有必要；边界层内的M数沿壁面法向变化非常快；不同壁温条件和不同的流动Re数均会改变边界层的厚度。
Based on the N-S equation, an advanced vector flux splitting algorithm is used to simulate the flow field in subsonic supersonic nozzle. In this paper, the computational efficiencies of several different computational formats are compared, and the direct method of solving the supersonic dominated mixed flow is given. Computation using algebraic turbulence model, transonic section of the calculated results with other experiments and calculations were compared. In the calculation, it is necessary to treat the exit boundary conditions subsonic, supersonic and backflow respectively; the number of M in the boundary layer changes very fast along the normal direction of the wall; and different wall temperature conditions and different flow Re numbers will change the boundary The thickness of the layer.