声速的

An air-breathing valveless PDE model was designed and manufactured,which was made up of subsonic inlet,mixing chamber,ignition chamber,detonation chamber and nozzle.

设计制造了完整的吸气式无阀脉冲爆震模型机，包括亚声速进气道，混合室，点火室，爆震室和喷管。

The second part of this paper presents a CFD-simulation of the performance of straight-walled and curved-walled micro nozzle/diffuser by FLUENT software. Such nozzle/diffusers are mainly used in micro venturi and also applied to valveless micropumps.

而在速度分布部分，当流量为5.338 mg/min时，宽度为150微米的喉部区流速已经高於声速，随后因速度不断增加，空气黏滞力影响了速度分布而产生了速度冲击现象。

To research the ways of relieving inlet unstart phenomenon, the flow of a typical hypersonic 2-D inlet with different suction positions was analyzed in this paper.

对某典型二元高超声速进气道流场进行了二维数值模拟，研究了抽吸位置及抽吸流量对进气道性能的影响。

The supersonic flow and combustion were simulated by the method of large eddy simulation.

并采用大涡模拟方法数值模拟了超声速流场中气动斜坡的流动及燃烧特性。

The results demonstrated that supersonic airflows will form a low-frequency oscillation in the combustor after the inlet cover is open, and the attenuation of the oscillation is very slow.

计算结果表明，在进气道整流罩打开以后，超声速气流会在燃烧室通道内形成振幅衰减较慢的低频剧烈振荡。

The results show that the cavity can change the waves in combustors,and facilitate the mixing of hydrogen and air for easier combustion.

采用有限体积法求解可压缩N-S方程及组分方程，对三种不同结构的超声速燃烧室进行了数值研究。

For example, when passing at low altitude supersonic aircraft, when the head and tail of the aircraft will have the pressure and density of mutations through the surface formed after the N-shaped shock wave reflection, reached the ground sounds like explosions, this special sound of noise is called the H -.

例如，当超声速飞机在低空掠过时，在飞机头部和尾部会产生压力和密度突变，经地面反射后形成N形冲击波，传到地面时听起来像爆炸声，这种特殊的噪声叫做轰声。

As a result, the thrust of ramjet drops and can not meet the needs of propulsion requirement for hypersonic flight.

导致冲压发动机不适应高超声速飞行器的推进要求。

The progenitor of the WR star may be a RSG moving eastward supersonically with the wind shocking against the ISM before hitting upon the molecular clouds. About~10〓yr ago.

该星的前身星，根据演化理论，可能是一红超巨星，向东以超声速运动，其星风与星际介质形成了弓激波，后来碰上分子云。

The normal angle of attack and bank angle were corrected according to the aerodynamic coefficient errors between the estimated values and the normal ones.

研究了气动模型存在误差情况下高超声速再入机动飞行器的制导律设计问题。

The split between the two groups can hardly be papered over.

这两个团体间的分歧难以掩饰。

This approach not only encourages a greater number of responses, but minimizes the likelihood of stale groupthink.

这种做法不仅鼓励了更多的反应，而且减少跟风的可能性。