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。
Increasing speeds above Mach 1.3 results in only small changes in shock wave strength.
这种汇合（或马赫）波的性质与前面所叙述的一般冲击波相同。
The behavior of this fused or Mach Wave is the same as that previously described for blast waves in general.
另外，推测了马赫数4拟似冲击波非对称的原因。
Moreover, the reason that Mach 4 oblique shock wave is asymmetric is conjectured.
这种汇合（或马赫）波的性质与前面所叙述的一般冲击波相同。
The behavior of this fused or mach wave is the same as that previously described for blast waves in general .
水平支管中马赫反射三波点迹线始于右尖点下游。
The triple-point trajectory characterizing Mach reflection locates downstream of the right corner in the horizontal branch.
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.
爆轰波爆点位置在对称轴上并不是固定的点，而是随着初始激波马赫数的变化而发生移动；
The initiation point is not fixed on the focusing point but varies with the incident shock Mach number.
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 ）。
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, …
研究表明，进气道溢流口位置是影响内乘波进气道起动能力的重要因素：在溢流口位置由两侧改至最下端后，起动马赫数由3.6下降为3.3；
The start Mach number reduces from 3.6 to 3.3 when the flooding position is changed from sides to bottom, further to 3.25 with one modular inlet.
研究表明，进气道溢流口位置是影响内乘波进气道起动能力的重要因素：在溢流口位置由两侧改至最下端后，起动马赫数由3.6下降为3.3；
The start Mach number reduces from 3.6 to 3.3 when the flooding position is changed from sides to bottom, further to 3.25 with one modular inlet.
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