在跨音速马赫数范围内需要经验结果。
它显示了飞行速度和马赫数。
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.
热空气可使之在超过临界马赫数之前达到更快的速度。
The hot air permitted higher speeds before the critical Mach number was exceeded.
并给出了膨胀比与喷嘴出口马赫数之间的幂指数关系。
A power correlation between expansion ratio and Mach number at the nozzle outlet was found.
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 shock total pressure was estimated with the normal component of the Mach number using normal shock theory.
风洞流场参数—总压、马赫数之间存在严重的耦合关系。
There exist a close coupling relation between the wind tunnel flow field parameters, total pressure and Mach number.
航弹主要是在稠密的大气层中飞行，巡航马赫数一般在0.9附近。
The aviation bomb is flying in the high density atmosphere layer. Its fight Mach number is generally 0.9.
利用一个核心加热器，可以有效地避免空气成分在较高马赫数时发生冷凝。
A hot core heater would be very useful to avoid condensation of the constituents of air at the higher Mach Numbers.
角振幅增大会使返回舱的平均俯仰阻尼增加，马赫数增大使俯仰阻尼降低。
The average effective pitch damping increases with increasing Angle of oscillation amplitude and decreases with increasing Mach number.
书针对化学工程应用，并且从而这热局限于是可压缩的流动（低的马赫数）。
The book is aimed at chemical engineering applications, and consequently it is limited to thermally compressible flows ( low Mach numbers).
文中还介绍了可压缩平面混合剪切层计算域在不同出口马赫数下的边界条件。
The boundary conditions under different Mach numbers of the outflow are described in detail.
在这里，气速对应到一个马赫数之一，指该流速等于当地音速的，特别是天然气。
Here the gas velocity corresponds to a Mach number of one, denoting that the flow velocity is equal to the local speed of sound of the particular gas.
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。
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.
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。
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.
本文在稳态等离子体装置中，对离子声孤立子的激发、空间传播和马赫数等进行了研究。
The properties of ion-acoustic soliton such as its excitation, spatial evolution aad Mach number are studied on a stable plasma device.
对某可调混压进气道在不同攻角、不同马赫数、不同斜板角度下进行了大量的数值计算。
At different attack angles, Mach Numbers and ramp angles, the numerical calculations of inner and external flow field are performed for an adjustable mixed compression inlet.
本文介绍这种变开闭比斜孔壁的概况和马赫数0.6到1.2范围内的初步校测试验结果。
This paper describes the general characteristics of the variable porosity walls and the preliminary results of calibration at Mach Numbers ranging from 0.6 to 1.2.
采用数值模拟技术详细地研究了不同掠高的某蒸汽轮机末级前掠叶片表面等熵马赫数的分布。
The numerical simulation technique is used to investigating the isentropic Mach number distribution on the different swept height blade surfaces of a turbine last stage blades.
介绍了小马赫数下弱可压缩流体流动的模型，对该模型的数值求解方法和应用情况也做了叙述。
The paper introduce a weakly compressible flow model for small Machnumber. Both corresponding numerical solutions of the method and the applications are given.
分析了来流马赫数、出口反压、攻角、高速旋转等因素对进气道流场结构及主要性能参数的影响。
And then the influence of the inlet flow's Mach, the outlet pressure, Angle, high velocity to the structure and major performance parameter of inlet's flow field are analyzed.
研究结果表明，当飞行马赫数小于设计马赫数时加速器模式的磁控进气道可以提高进气道的性能。
It can be concluded that the accelerator mode MHD-controlled inlet can improve the inlet performance when the flight Mach number is lower than the design value.
针对抗性消声器中扩张结构和尾管引起的射流噪声问题，建立了低马赫数射流噪声有限元分析模型。
Aimed at the jet noise which is induced by the expand structure and tail tube in the resistant muffler, a finite element model at low Mach number was developed.
并以燃烧室的进口马赫数是2.2为例，对燃烧室的工况、壁型及参数变化进行了详细的分析研究。
As example, the operating regime, wall profile and performance parameters of supersonic combustors with entry Mach number 2.2 are computed in some detail.
随着对流马赫数的增加，脉动的偏斜性和间歇性略有增加，并且其峰值对应的位置向混合层外侧移动。
With increasing convective mach number the skewness and flatness factors increase a little and the peak positions move outwards.
随着对流马赫数的增加，流向脉动强度变化不大，横向和展向脉动强度减小，混合层的扩张率随之减小。
With increasing convective Mach number the streamwise fluctuation intensity varies little but the transverse and spanwise intensity along with the thickness growth rate decrease.
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。
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。
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.
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