但是这个分压是总压强的函数。
这分压等于气相中b的摩尔分数，乘以总压强。
It's the molar fraction of B in the gas phase times the total pressure.
总压强P等于惰性气体的分压，与A物质的蒸汽压之和，在我们的例子中总压强是一个大气压。
Such that the sum of the partial pressure of the inert gas, plus the partial pressure of A, is the total pressure. One bar, in our case.
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.
本文通过数值计算的方法研究插板式总压畸变试验技术。
The numerical calculated method was used to research the technology of the total pressure distortion with flashboard.
研究表明，该类进气道在各种侧滑状态下总压恢复系数较高。
The results show that this type of inlet has high total pressure recovery coefficients at a wide range of yaw angle.
压气机叶型气动优化设计目标是静压升最大和总压损失最小。
The maximization of the static pressure rise and minimization of the total pressure loss are taken as the design targets.
截面平均总压和周向低压区内平均总压与进气流量成线性关系。
The section average total pressure and the average total pressure in the circumferential low-pressure areas are in linear relationship with the air inlet flow.
若密度比、静温比相同或相近时，速度差对总压损失的影响可忽略。
The effect of the velocity difference on total pressure loss may be neglected, if the density and the static temperature difference are equal.
介绍进气总压畸变对双轴涡喷发动机性能和稳定性影响的试验及其结果。
A brief view and results of tests for the effects of the inlet total pressure distortion on the performance and the stability of a two-spool turbojet engine are presented.
分离区仅是高总压损失和高熵值的低能流体聚集区，而非高损失来源区；
Moreover, the separation zone is only a low-energy fluid gathering area for large total pressure loss and entropy rather than a zone of loss source.
静压和总压的分布规律比较相近，沿半径方向的分布呈现较好的轴对称性。
The static pressure distribution is similar to the total pressure, and they all show symmetry along the radius direction.
介绍了1种分析进口总压畸变对多级轴流压气机特性影响的逐级模拟方法。
A stage - by - stage simulation method is introduced for analysis of inlet total pressure distortion effect on the multistage axial flow compressor characteristics.
通过叶片表面总压损失系数，证实了先进叶型在流动中可以降低叶型损失。
It is proved that the profile loss can be decreased with the use of advanced blade through the comparison of loss coefficient of blade surface overall pressure.
扩张角的增加可提高速度环量，但是流动混合损失增加，总压恢复系数减小。
The increase of lobe diffusion angle results in the increase of velocity circulation at the lobe exit section, but it raises the mixing loss and lowers the pressure recovery coefficient.
以总压恢复系数最大为目标，采用等激波强度和等激波角设计方法建立进气道模型；
The inlet design calculating model was set up based on the theory of equal shock wave intensity and angle of supersonic airflow to get maximum total pressure coefficient.
以压气机出口总压作为喘振检测特征信号，采用时间序列分析方法建立了AR模型。
The compressor exit total pressure is adopted as a characteristic signal to detect surges. An ar (autoregressive) model is constructed with the time series analysis method.
试验表明其出口平均总压恢复系数较低，周向总压畸变指数较大，旋流较强且很不规则。
Test results show lower exit average total pressure recovery, larger circumferential total pressure distortion and stronger and more irregular secondary flow.
在吊舱进气道进口安装扰流板进行试验，研究扰流板进气畸变的影响因素及总压畸变特征。
Characteristics and influence factors of total pressure distortion are studied based on tests conducted on a disturbed board installed in the nacelle inlet.
由于喷流方向与主流方向夹角较小，总压损失也较物理斜坡、横向喷流等混合增强方式小。
Due to the smaller Angle of injection, the ratio of total pressure loss of aerodynamic ramp is less than the physical ramp and transverse injection stream.
分析在不同叶片安装角下，叶片表面静压系数、出口总压损失系数和出口气流角的变化规律。
The static pressure loss coefficients, total pressure loss coefficients and flow outlet Angle distribution are simulated in conditions of different setting angles.
笔者自行设计研制了用于高超声速推进风洞流场测量的带有水冷装置的可移动式扫描总压耙。
A kind of scan pitot-pressure rake with water cooler was designed in IMCAS for the hypersonic propulsion wind tunnel flow measurement.
在风洞中模拟底排实验，通过测量和控制流量计前介质总压，获得了较高准确度的底部排气率。
In wind tunnel test, the base bleed ratio of higher accuracy is obtained by measuring and controlling the total pressure of the bleed medium in front of flowmeter.
针对不同的发动机点火状态，在射流轴线的不同距离上对一系列测点位置的总压参数进行了测量。
According to the different motor ignition states, a series of total pressure values of observed points on the respective jet axis distances was measured.
本文首先导出粘性不可压缩流动的新的总压方程，然后采用隐式方法对该总压方程进行数值计算。
Firstly, a new total pressure equation of the viscous incompressible flow is introduced in this paper. Then, this equation is numerically computed by use of the implicit method.
经优化后，透平高压级静叶的总压损失系数减少0.95%；多级压气机整机效率提高2.1%。
After optimization, the total pressure loss of the turbine vane was reduced by 0.95%, and the efficiency of the overall compressor was increased by 2.1%.
结果表明：在满足设计预期目标的同时，炉内单质硫生成量得到提高，总压降损失得到降低，具有节能效果。
The results showed that formation of sulfur furnace is improved and the total pressure drop is reduced which meet the design expectations with energy-saving effect.
结果表明：在满足设计预期目标的同时，炉内单质硫生成量得到提高，总压降损失得到降低，具有节能效果。
The results showed that formation of sulfur furnace is improved and the total pressure drop is reduced which meet the design expectations with energy-saving effect.
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