采用数值分析方法分析了跨声速喷管无粘流动和超声速射流对挡流板的冲击流场。
Numerical analyses of the transonic nozzle inviscid flow and supersonic jet impingement on a jet TAB are presented.
主流区无粘流动采用了边界元法计算，粘性流动区采用附面层理论的积分关系式计算。
Boundary element calculation is applied to the main flow field, while integral methods of the boundary layer theory are applied to the viscous layers.
因此，方程(8.2)，(8.6)，(8.10)是一维、定常、绝热、无粘流动的控制方程。
Thus, Eqs. (8.2), (8.6), (8.10) are governing equations for one-dimensional, steady, adiabatic, inviscid flow.
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