超音速风洞

CCD图像系统与实时全息技术在超音速风洞流场显示中的应用

The application of CCD image system and real-time holometry to flow visualization in supersonic wind tunnel

热线探头在中国空气动力研究与发展中心（CARDC）FL-23跨超音速风洞中进行了校准。

Hot-wire probes have been calibrated in FL-23 transonic and supersonic wind tunnel of CARDC ( China Aerodynamics Research and Development Center ) .

在超音速风洞实验室，用来流风速27m／s和33m／s，测试1号雾化头转速依次为7460、9350r／min；

And No. 2 rotary atomizer were tested in the laboratory wind cave of supersonic speed of 27 and 33 m / s. The rotational speed of No.

氦氖激光全息术在超音速风洞流场定量显示中的应用

Application of He-Ne Laser Holography in Quantitative Visualization of Supersonic Wind Tunnel Flow Field

超音速风洞喷管设计中的边界层修正的新方法

A new method of boundary layer correction in the design of supersonic wind tunnel nozzle

低密度超音速风洞大约开始发展于1960年。

Hypersonic wind tunnels operating at very low densities were developed starting in about 1960 .

离心压气机无叶扩压器内部流动的实验测量和数值分析超音速风洞扩压器激波串现象的数值模拟

Experimental Measurements and Numerical Simulations of the Internal Flow Field in Vaneless Diffuser of a Centrifugal Compressor

杆形头部弹丸的超音速风洞试验研究超音速变形轰炸机

Experimental studies of blunt shells equipped with nose spike in a supersonic wind tunnel the supersonic shape-shifting bomber

自补偿光亮电刷镀镍技术及其在超音速风洞表面强化中的应用

Characteristics of Self-Replenishing Bright Nickel Brush-Plating Solution and Its Application in the Surface Strengthening of an Ultrasonic Aerodynamic Designing Equipment

重复性实验结果表明，该装置可用在跨超音速风洞中测量飞行器模型的俯仰阻尼导数。

The results obtained in repeated tests show that this test mechanism can be used to measure the pitching damping derivatives for the vehicle models in the transonic and supersonic wind tunnel .

同时还研究了在对超音速风洞中复杂流场数据严重不完全的情况下的重建，提出了正交窗口小角度范围采样和充分利用先验知识的多信息融合重建方案。

For the reconstruction in the case of severely incomplete data of flow field under wind tunnel , the orthogonal projection data collection method of limited angle and information amalgamation reconstruction using transcendental knowledge have been proposed .

超音速电弧风洞探针信号的分析

Analysis of Probe Signals in Hypersonic Arc Heated Tunnel

本文介绍一个单支点半柔壁喷管的超音速进气道风洞。喷管出口的尺寸是160毫米×160毫米，试验M数范围为1.6～2.6，攻角变化范围为15°（单向）。

Herein given is a description of a newly built single jack , semi-flexible nozzle supersonic intake tunnel , the nozzle exit of which is 160 × 160mm with a range of Mach-number 1.6-2.6 and that of nozzle pitching 15 ° .

尖拱圆柱体弹丸超音速马格纳斯效应风洞实验研究橄榄体上表面波分析

An Experimental Investigation of the Magnus Effect of the Ogive Cylinder in the Supersonic Wind Tunnel Analysis of Surface Wave on an Ogive