[计] 显式引用;
The chamber-nozzle subsonic-transonic flowfield of solid rocket motor is computed by time-dependent method. The governing equations are numerically solved by MacCormack explicit scheme. The parameters of boundary points are calculated with physical boundary conditions and characteristic equations on the reference plane.
本文用时间相关法计算了固体火箭发动机燃烧室&喷管亚跨声速流场数值解,控制方程用MacCormack二步显格式:边界点参数用物理边界条件和参考平面上的特征方程计算。
Implicit reference points need be made explicit.
隐含的数据必须明朗化?明确指出参考数据的性质.
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