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还有,这是一个音速感应器。This is a subsonic impact sensor.

我实在不明白什么是亚声速。I have no idea what subsonic speed is.

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还有个玩意儿。这是个次音速冲击传感器。One more thing. This is a subsonic impact sensor.

不过,后休克的流动,在射流仍会亚音速。However, after the shock the flow in the jet will still be subsonic.

这些现象也反映了燃烧室内亚音速流场的性质。These phenomena are controlled by the nature of the subsonic flow field.

另一种是爆燃,或者又称亚音速燃烧,这种方式很少产生爆炸。The other is deflagration, or subsonic burning, which causes little or no blast.

亚音速进气管是用于某课题仿真模拟试验设备的关键部件,设计技术要求高,制造难度大。Subsonic intake pipe is the key test device for a pre-research project simulation test.

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本方法是基于对FW-H方程的准确求解,并限制螺旋桨叶尖相对速度为亚音速。The blade tip speed is limited to subsonic. The formulation is based on the FW-H equation.

因此,有必要对亚音速飞行器的导航方案进行改进。Therefore, it is necessary to improve the current navigation means of the subsonic vehicle.

本文介绍了某型飞机前掠翼气动布局的低速风洞实验结果。This paper gives a brief account of the subsonic experimental investigations of FSW models.

在众多的亚原子粒子家族中,中微子是最令人捉摸不定的基本态粒子。Neutrino is the most unstable elementary state particle in numerous subsonic atom particles.

分析了支线民航机一种新型亚音速带有腔室旁通道的进气道的几何形状设计和气动试验结果。The intake with plenum bypass is a new type subsonic intake for civil medium range aircraft.

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亚音速飞行器具有飞行速度低,飞行时间长,低动态的特点。The subsonic vehicle has the characteristics of low speed, longtime flight and low dynamics.

当这种“转向翼飞机”恢复亚音速飞行时,机翼就转回垂于直机身的角度。When the Switchblade returns to subsonic speeds, the wing will rotate back to perpendicular.

给出计算栅格翼和机身组合体亚超音速气动力干扰理论方法。Aerodynamic analysis is made for grid fin-body configurations in subsonic and supersonic flow.

导弹以雷达高度计控制在40-60米的高度以高亚音速飞向目标。It flew to the target at an altitude of 40-60 m using a radar altimeter at a high subsonic speed.

但在可预见的未来,亚音速飞机的形状不会发生根本的改变。But it is unlikely that the shape of subsonic aircraft will change radically in the foreseeable future.

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它的次音速飞行能力高达1.2万米,攻击距离至少为直径2000公里。It's capable of subsonic flying as high as 12 thousand meters with an attack range of at least 2000 kilometers.

在低亚音速范围,后体阻力基本不变化,随着马赫数增加至跨音速,出现激波阻力。The drag of aftbody keeps constant in low subsonic flow, but increases in transonic flow due to the shock wave.

采用计算气动声学方法研究了管道近音速区的声传播和声波与激波的相互作用问题。A computational aeroacoustics approach is applied to studying sound propagation in subsonic and supersonic nozzle.