1.
A review of heat exchanger study for large-scale continuous transonic wind tunnels
大型连续式跨声速风洞热交换器概述
2.
Research of Second Throat Design of Continuous Transonic/Supersonic Wind Tunnel
连续式跨声速风洞第二喉道设计技术研究
3.
Floating suspension system for full model flutter test in transonic wind tunnel
跨声速风洞全模颤振试验悬浮支撑系统
4.
Research of data process methods and model excitation for transonic flutter experiments in wind tunnel
跨声速风洞颤振试验模型激振与数据处理方法研究
5.
The test technique for aircraft with high aspect ratio in the 2.4 meter transonic wind tunnel
2.4米跨声速风洞大展弦比飞机测力试验技术研究
6.
Aeroelasticity Matters: Some reflections on Two Decades of Testing in the NASA Lanley Transonic Dynamics wind Tunnel.
气动弹性问题：NASA兰利跨声速动力学风洞20年试验的几点思考。
7.
The wind Tunnel/flight Correlation panel discussed the validation of the National transonic Facility (NTF) in the following order.
风洞与飞行相关性小组按下列顺序讨论了国家跨声速设备（NTF）的鉴定工作。
8.
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)
9.
The Test and Calibration of Φ200 Hypersonic Wind Tunnel
Φ200高超声速风洞调试和流场校测
10.
An investigation of background noise measurement technology in aeroacoustic wind tunnel
低速航空声学风洞背景噪声测试技术研究
11.
The Design and Experimental Studies of Supersonic Straight Through Wind Tunnel and "Supersonic-supersonic" Mixing Layer Wind Tunnel;
直连式超声速风洞与“超—超”混合层风洞的设计和实验研究
12.
Aero-Acoustic Experimental Investigation of the Cavity Flow Fields in High Speed Wind Tunnel;
高速风洞弹舱流场气动声学特性试验研究
13.
Mach Number Seven and Eight Nozzle Design of the Diameter One Meter Hypersonic Wind Tunnel and Flow Field Testing;
Φ1米高超声速风洞M7、8喷管设计及流场校测
14.
Way of Improving Aerodynamic Load Coefficient of Transonic Axial Fan Rotor
提高跨声速风扇转子气动负荷系数途径
15.
The experimental results of low temperature ablator (beeswax and camphor) tests in the hypersonic wind Tunnel are presented in this paper.
本文给出了低温烧蚀材料的高超声速风洞烧蚀实验研究的结果。
16.
Development of Experimental Power Source and Temperature Control System for Φ1m Hypersonic Wind Tunnel;
Φ1米高超声速风洞加热器试验电源及温控系统设计
17.
Experimental Investigation of Fixed-geometry Two-dimensional Mixed-compression Supersonic Inlet with Twin-inlet 90° Configuration at Venter
双下侧定几何二元混压式超声速进气道的风洞试验
18.
Although strain gage balances have been most useful in transonic and supersonic tunnels, they are by no means excluded from lowspeed work.
虽然，应变天平最适用于跨超音速风洞，但丝毫不意味着不能用于低速实验。