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。
This oblique configuration redistributes the shock waves that pile up in front of a plane at Mach speeds and cause drag.
这种倾斜的外形把超音速飞行时集中在飞机前部并形成阻力的冲击波重新分布。
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；
An experimental investigation on effects of oscillating shock generated by liquid jet on reinforcement of hydrogen-fueled supersonic combustion in Mach 2 airstream was completed.
研究了在燃烧室入口马赫数为2的超音速燃烧中，液体射流所产生的振荡激波对强化超音速燃烧的作用。
It was observed that the average values of Mach Numbers and pressures were almost constant from the entrance of the isolator to the onset of shock train along the isolator.
研究发现，在不同反压下隔离段中的平均马赫数和平均压力值，从隔离段进口到激波串波前基本保持不变。
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 ）。
The shock total pressure was estimated with the normal component of the Mach number using normal shock theory.
激波总压损失用正激波关系式通过马赫数法向分量估计。
The transition of leading shock from regular reflection to Mach reflection respectively happens in the horizontal and vertical branches.
在水平和垂直支管中，诱导激波出现由规则反射向马赫反射转变。
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。
The results indicate that passive control technique can reduce peak Mach number on the surface of the airfoil and reduce the adverse pressure gradient, shock is also weakened.
结果表明，被动控制使得沿模型表面的马赫数峰值及过压力梯度明显减小，激波减弱。
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。
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。
The initiation point is not fixed on the focusing point but varies with the incident shock Mach number.
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.
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；
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