声速流导,sonic conductance
1)sonic conductance声速流导
1.In order to obtain accuratesonic conductance of solenoid valve,a polytropic exponent was used during the data processing in the discharge method for measurement pneumatic component flow rate characteristics.为准确得到电磁阀的声速流导,把多变指数引入放气法测试气动元件流量特性的数据处理过程。
2.The necessity of usingsonic conductance C and critical pressure ratio b to describe the flow rate characteristics of pneumatic components was discussed firstly,then the principles and the test device of ISO/DIS6358 standard were introduced and its advantages and disadvantages were analyzed.论述了利用声速流导C与临界压力比b描述气动元件的流量特性的必要性,介绍了ISO/DIS6358标准的原理及试验装置,分析了其优缺点,参考等温容器放气法替代ISO标准测试方法,介绍了等温容器放气法的试验装置和方法及测试原理。
3.According to ISO6358 which is concerned with the definition of two parameters, that issonic conductance C and critical pressure ratio b for flow characteristics of pneumatic components, calculating methods of C & b for air tube are derived from theoretical analysis.根据ISO6358关于流量特性参数声速流导C值和临界压力比b值的定义,结合相关气动理论,给出了气管道流量特性参数的计算方法,并编制了相应的计算机程序进行了仿真。
2)supersonic flow超声速流
1.Quasisteadystate three shock wave structures in thesupersonic flow are researched.对超声速流中准稳定三波结构进行了研究,该结构中主激波以一定的速度D→沿超声速流运动,它不但引起相应的反射激波运动而且会使激波后气流中的一系列气动力参数发生变化,包括总压、总焓和熵等。
2.A number of numericalIv com-puted examples on the airfoils at transonic andsupersonic flows demon-strate that the present m.对翼型的跨超声速流动算例表明，本法具有较好的稳定性和能有效地抑制激波两侧振荡。
3.A Computational model for predictingsupersonic flowfield with separattd subsonic reglon caused bv convex axisymmetric back-ward-facinq step is presented.计算结果给出了与实验值吻合的物面压力分布以及超声速流场的流动图画。
英文短句/例句
1.Aerodynamic Flutter and Limited Cycle of a 2-D Wing in the Hypersonic/Supersonic Flow Field超声速/高超声速流中二元机翼的颤振与极限环
2.Bifurcation Analysis of the Airfoil with Cubic Nonlinearity in Supersonic\Hypersonic Flow超声速及高超声速流中立方非线性机翼的分岔研究
3.On the parameters optimum of three shock wave structure in the supersonic flow超声速流中三波结构的参数优化研究
4.Velocity gradient in Kelvin-Helmholtz instability for supersonic fluid超声速流体Kelvin-Helmholtz不稳定性速度梯度效应研究
5.beam-deflection ultrasonic flowmeter声速偏转式超声流量计
6.numerical solution for inviscid supersonic flow超声速无粘绕流数值解
7.Turbulence Model for Hypersonic Complex Flows高超声速复杂流动中湍流模式的研究
8.Numerical Simulation for 3-D Hypersonic Flows on Hybrid Meshes and Parallization;三维高超声速绕流流场并行算法研究
9.Stability Characteristics of the Boundary Layer of an Axisymmetric Blunt Nosed Cone in the Supersonic and Hypersonic Flow超声速高超声速球锥绕流的边界层稳定性特点初探
10.The Method of Time-Domain Correlation Ultrasound Detect Blood Flow Velocity超声检测血流速度的时域相关方法
11.Using Roughness Surface on Control of Supersonic Laminar Flow Boundary Layer用表面粗糙度控制超声速层流边界层
12.Study on Flow Controls for Hypersonic Flying Vehicle Fuselage/Propulsion高超声速飞行器/发动机流动控制研究
13.Flow field calibration of NUAA Φ0.5m hypersonic wind tunnel南航Φ0.5m高超声速风洞流场校测(英文)
14.The Test and Calibration of Φ200 Hypersonic Wind TunnelΦ200高超声速风洞调试和流场校测
15.Analysis of Characteristics of Supersonic Speed Ramjet Isolator Inner Flow Fields超声速冲压发动机隔离段内流场分析
16.Research on dynamic characteristics of underwater superasonic gas jets水下超声速燃气射流动力学特性研究
17.Numerical Simulation of External-Compression Supersonic Inlet Flow Fields外压式超声速进气道流场的数值模拟
18.Research on the Supersonic Two Phase Flow Liquefaction Equipment超声速气液两相流液化升压装置研究
相关短句/例句
supersonic flow超声速流
1.Quasisteadystate three shock wave structures in thesupersonic flow are researched.对超声速流中准稳定三波结构进行了研究,该结构中主激波以一定的速度D→沿超声速流运动,它不但引起相应的反射激波运动而且会使激波后气流中的一系列气动力参数发生变化,包括总压、总焓和熵等。
2.A number of numericalIv com-puted examples on the airfoils at transonic andsupersonic flows demon-strate that the present m.对翼型的跨超声速流动算例表明，本法具有较好的稳定性和能有效地抑制激波两侧振荡。
3.A Computational model for predictingsupersonic flowfield with separattd subsonic reglon caused bv convex axisymmetric back-ward-facinq step is presented.计算结果给出了与实验值吻合的物面压力分布以及超声速流场的流动图画。
3)acoustic streaming velocity声流速度
4)transonic flow跨声速流
1.The measurement of spontaneously condensationdroplet intransonic flow;跨声速流自发凝结水滴的测量
2.The applications as carried out by DLR range from low speed flows totransonic flows, from high lift configurations to propellers and rotor.DLR(德国宇航研究院)对这些技术的应用包括从低速流到跨声速流、从增升装置到螺旋桨和旋翼、从弹射装置和水塔储水罐尾迹流旋涡到三角翼上涡破裂现象等的研究。
3.A method of deduce the wind tunnel flexible wall nozzle throat has been used in FL24 wind tunnel to gain the M≥1 uniformtransonic flow field with the big percentage blockage captive trajectory supports in the wind tunnel.2m)跨超声速风洞中,通过采用减小风洞柔壁喷管喉道截面积的方法,成功地在风洞超扩段内装有大堵塞度六自由度机构情形下建立了均匀M≥1跨声速流场。
5)subsonic flow亚声速流
6)free-streaming[物]声速流
延伸阅读
脉心导敏 ,脉导敏,英他佐明,麦新导明药物名称：吗多明英文名：Molsidomine别名： 吗导敏;吗多明;吗斯酮胺;脉心导敏 ,脉导敏,英他佐明,麦新导明外文名：Molsidomine 特点： 脉导敏是一种属于亚胺类化合物，其作用与硝酸盐相似。舌下含服1毫克，2～4分钟起作用，可阻止心绞痛发作。口服一次可持续6～7小时，剂量每天3次，每次2毫克。副作用包括头痛、头胀、脸部发热感等，但不多见。 适应症： 防治心绞痛的发作。 用量用法： 口服：１次１～２ｍｇ，１日２～３次，发作时舌下含服：１次２ｍｇ。喷雾吸入：每次揿吸１～２次（相当于本品０．２～０．４ｍｇ），每日次数酌定。 注意事项： 1.一般不良反应可有头痛、面部潮红、眩晕等，停药后可自行消失。 2.低血压、青光眼病人忌用。 规格： 片剂：每片１ｍｇ、２ｍｇ。 气雾剂：每瓶含４２ｍｇ（可揿吸２００次左右）。 类别：非选择性钙通道阻滞剂||防治心绞痛药
