P SI8400电子压力测试系统是美国压力系统公司生产的高精度的压力测量设备，广泛应用在风洞压力测量试验中。
PSI8400 pressure test system is of high precision pressure measurement equipment produced by PSI Inc. of USA and it is used in pressure measurement test of wind tunnel widely.
它广泛用于瞬态压力测量，如冲击管、风洞以及地震仪器设备中。
It is used in measurement of pressure transients, such as in shock tubes, wind tunnels, and seismograph equipment.
本文介绍了可用于测量风洞中旋转模型表面压力分布的集成测试系统。
The paper introduced a spinning model surface pressure measurement sy which used in the wind tunnel.
为配合多功能风洞中边界层测定的课题，建立一个压力微机采集系统是十分必要的。
It is indeed necessary to build a personal computer collecting system of measuring pressure in order to measure the boundary layer in a multifunctional wind tunnel.
尽管该风洞的尺寸很小，我们仍对翼型表面压力分布试验段的研制工作进行了大胆的尝试。
Although it is very small in size, some developments in the test section of pressure distribution on airfoil surface have been attempted.
实验是在日本室兰工业大学的压力—真空型超声速风洞中进行的。
The experiment was done in the pressure-vacuum supersonic wind tunnel of Muroran Institute of Technology of Japan.
本文介绍了一种在激波风洞中取得的，装在钝锥模型上的控制翼热流及压力特性实验结果。
This paper presents experimental results of flap heat transfer and pressure characteristics on a blunt cone in shock tunnel.
介绍了国内首次在高速风洞中使用荧光压力传感器(LPS)技术对飞机模型机翼表面压力场测量的初步结果。
The pressure field measurement results on the wing surface of airplane model by luminescence pressure sensor (LPS) technique and classic tap technique in high speed wind tunnel are presented.
在风洞用电子扫描阀进行测压 ，研究了绕平板扰流片和锯齿扰流片分离流动的壁面压力分布 。
Wall pressure distribution induced by the saw-tooth flap has been investigated with electronic pressure scanner in wind tunnel.
将数值预测的压力场与实测结果及缩尺模型风洞试验数据进行了比较，分析了风洞试验与场地实测之间、数值模拟与试验之间的异同，得到一些有参考价值的结果。
Based on the analysis of the differences between wind tunnel test and field measurements and the differences between numerical results and test data, some referential conclusions are drawn.
利用同步多点压力扫描技术对一个圆拱顶屋盖进行了风洞试验。
Wind tunnel tests of a dome like roof were carried out by means of the synchronous multi-pressure scanning technique.
在风洞中对水下航行体模型尾部壁面脉动压力与近壁湍动速度进行同步测试及处理分析。
The wall pressure fluctuations and near-wall turbulent flow were jointly measured at the stem of an underwater vehicle model in CSSRC Wind Tunnel.
在风洞实验中采用纹影照相和压力分布相结合的实验方法，确定了侧后向喷流复合增程技术中喷嘴—模型之间间隙的大小对表面压力的影响。
The influence of clearance between the nozzles and the model of the surface pressure was used in the hybrid extended-range technique of the side back jet.
风洞顶壁上最佳测压点非定常压力迟滞环方向与风洞底壁上对应最佳测压点非定常压力迟滞方向相反。
The hysteresis direction at the optimum measuring pressure point on top wall is opposite to that on bottom wall.
实验中，自主设计了高超声速直联式风洞模拟自由来流马赫数5.3，通过测量进气道上壁面压力分布，研究了进气道开启过程的起动特性；
During experiment, a directly connected wind tunnel was independently designed to simulate a free stream Mach at 5.3, based on which the dynamic process of inlet opening was studied;
在马赫8炮风洞中开展了不同初始真空压力条件下风洞喷管启动过程对侧压进气道启动的影响研究。
Effect on inlet starting of nozzle starting process was studied in a 500 mm Mach 8 gun tunnel.
在马赫8炮风洞中开展了不同初始真空压力条件下风洞喷管启动过程对侧压进气道启动的影响研究。
Effect on inlet starting of nozzle starting process was studied in a 500 mm Mach 8 gun tunnel.
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