采用高斯消去法和欠松弛迭代法并应用计算机对这些方程进行数值求解，从而计算出各支路的流量。
The equations are solved numerically using the method of Gauss elimination and under-relaxation iteration by computor, thus the air flows in every branch are determined.
本文从化学非平衡粘性激波层控制方程出发，用数值法计算了高超音速钝体绕流头部区流场(包括驻点线和音速线)。
In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region (including stagnation line and sonic line).
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