在1995年，人们首次提出，长号能产生一种高能压力波，它的速度能略超音速。
It was first suggested in 1995 that the intense pressure waves, which can briefly exceed the speed of sound, could come from trombones.
地面实验设备必须要模拟高超音速飞行状态下气流的焓、压力、M数和空气中氧气的组分。
It is necessary to simulate the high enthalpy, high pressure, Mach number and the same concentration of oxygen species as air in hypersonic flight.
本文给出了计算1976标准大气表中温度、密度、压力、音速等诸参数的数学表达式。
A set of formulas has been developed to calculate the atmospheric temperature, density, pressure, the speed of sound etc. of Standard Atmosphere 1976.
在对油管合理地划分计算单元后，可求解得到油管各个结点在不同时刻的燃油音速、密度、压力和流速等特征参数值。
After partition the pipe into calculation cells, the sound velocity, fuel density, fuel pressure and flowing velocity at every calculation crunode in different time are gained.
其对应的音速与汽液两相流体的空泡率、压力及液相密度等因素有关。
Then the corresponding sonic velocity of the two-phase flow is determined by the void ratio, pressure and density of the liquid phase.
分析了两相流体中音速随压力、干度、汽隙率、相变系数等的变化关系，并从中得出了一些重要的结论。
The change of sound velocity with pressure, dryness degree, void-fraction, and phase-transition coefficient are analyzed. Some important conclusions are derived.
通过数值求解定常跨音速流的无粘、小扰动方程，根据实心翼型或多孔翼型的边界条件，获得了相应的压力分布。
By numerically solving the inviscid, small disturbance equation in steady transonic regime, with boundary conditions on solid or porous airfoils, the corresponding pressure distribution is obtained.
试验结果表明，气液两相流音速与气泡率、当地压力及其流型有关。
The result indicates that the sound speed is related to the void fraction, local pressure and flow pattern.
简要地介绍了亚音速飞机压力分布测量的飞行试验技术，并给出了部分试验结果。
Technique of in flight measurement of pressure distribution on a subsonic transport aircraft is introduced. Some flight test results are presented.
在颤振特性分析中所需要的广义气动力是根据亚音速非定常升力面理论，采用马蹄涡—振荡压力偶极子格网法计算的。
The generalized aerodynamic force required in analysis is calculated by using horse shoe vortex— vibrational pressure doublet grid method, based on theory of subsonic unsteady lifting plane.
通过对超音速汽液两相流在变截面通道中的升压过程的实验研究，得到了变截面通道内超音速汽液两相流的压力分布规律。
The process of supersonic steam water two phase flow in a channel with variable section is studied experimentally and the pressure profiles along the channel are obtained.
论文的工作由两部分组成：1．跨音速脉动压力预测与分析。
Two parts are included in the thesis:1 The Analysis and Prediction of Fluctuating Pressure at Transonic Mach Numbers.
但使用超音速引射器后，当球罐压力下降到某一值时会产生高频噪声，影响管束区操作环境。
Then the supersonic ejector is used, the high frequency noise will take place when the pressure in store tanks decreases to a specific value, and the environment of.
但使用超音速引射器后，当球罐压力下降到某一值时会产生高频噪声，影响管束区操作环境。
Then the supersonic ejector is used, the high frequency noise will take place when the pressure in store tanks decreases to a specific value, and the environment of.
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