Increasing speeds above Mach 1.3 results in only small changes in shock wave strength.
速度升高到1.3马赫（速度单位，1马赫=音速=340.29m/s——译者注）以后，不会再对冲击波强度造成太大的影响。
Moreover, the reason that Mach 4 oblique shock wave is asymmetric is conjectured.
另外，推测了马赫数4拟似冲击波非对称的原因。
The biggest lift drag ratio 3.36 considering viscous effects is obtained at Mach 6 when a proper base conical shock wave angle is chosen.
在设计点附近选取合适的半基准圆锥激波角并考虑粘性影响时，可得到乘波体最大升阻比为3.36；
The computational results are in a good agreement well with the experimental data of Mach number before the shock wave, separation and reattachment positions.
数值模拟结果，在激波强度、分离点位置和再附点位置等方面，与实验结果吻合较好。
This paper presents the surface characteristics of the inter-action between shock wave and turbulent boundary layer induced by sharp fin with emphasis on Mach number effects.
本文介绍了尖前缘翼诱导激波和湍流边界层干扰流场壁面特性，着重强调马赫数影响。
Stuldies on the Mach reflection of spherical shock wave produced by electric exploding metallic wire on rigid wall were carried out in this paper.
本文对金属丝电爆炸产生球面激波在固壁上的马赫反射作了研究。
The visualized results give the overview of explosive and shock, and some details about the transimssion of shock wave in the field, such as reflection, flow over an obstacle and Mach reflection, …
从可视化的结果中不仅可以展现爆炸与冲击过程的整体概貌 ，而且可以清晰的显示爆炸与冲击过程的细微过程 （如爆炸场中冲击波遇障碍物后的反射、绕流及马赫反射等 ）。
Pressure contours, density contours, Mach number contours and pressure coefficient on the cone are obtained. Conical shock wave position is geometrically determined.
获得波后流场的等压力线、等密度线、等马赫线和圆锥表面的压力系数，确定了锥激波的几何位置。
Pressure contours, density contours, Mach number contours and pressure coefficient on the cone are obtained. Conical shock wave position is geometrically determined.
获得波后流场的等压力线、等密度线、等马赫线和圆锥表面的压力系数，确定了锥激波的几何位置。
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