The experiment was done in the supersonic wind tunnel of Muroran Institute of Technology.
实验是在日本室兰工业大学的超声速风洞中完成的。
Moire tomography is applied to measure the complex density distribution in supersonic wind tunnel.
使用叠栅层析技术解决超音速风洞中复杂密度场的测量难题。
The experiment was done in the pressure-vacuum supersonic wind tunnel of Muroran Institute of Technology of Japan.
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 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.
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。
Then, the base bleed method is introduced on a general supersonic missile to decrease the base drag of the inlet cowl for the first time and is validated by wind tunnel test.
本文首次将底部排气法应用于导弹上，结合一种具有常规气动布局的超声速导弹进行了底部排气方案设计，采用一种“底窝器”来提高进气道整流罩的底部压强，并进行了风洞实验验证。
Flow characteristic of supersonic bi-cone inlet of ramjet assisted range projectiles is studied, and reasonable flow structures are also achieved through the wind tunnel experiment.
对某冲压增程弹用超声速双锥进气道流场特性进行研究，在风洞试验中得到合理的流场结构图谱及试验数据。
Instead of the sonic nozzle, low supersonic nozzles have been utilized to solve the choking problem in transonic wind tunnel testing of high angle-of-attack and high blockage.
本文介绍用低超声速喷管代替声速喷管，解决了大迎角大堵塞度跨声速实验时的风洞壅塞问题。
A fixed-geometry two-dimensional mixed-compression supersonic inlet with sweep-forward high-light and bleed slot in an inverted "X"-form layout was tested in a wind tunnel.
针对一种带放气槽的定几何二元倒置“X”型混压式超音速进气道进行了风洞吹风实验。
A basic idea of a quiet wind tunnel is described. A supersonic quiet wind tunnel (SQWT-120) is designed and built.
论述了静风洞概念并设计和建立了一座小型静风洞SQWT- 120。
The starting process of wind tunnel, involving turbulence, shock wave, low subsonic and high supersonic mixing flows, is a very complex transient process.
超声速风洞的起动过程涉及到湍流、激波及低亚声速和高超声速混合流动，是一个非常复杂的瞬态过程。
The shocklet was observed based on NPLS techniques in supersonic turbulent mix layer wind tunnel with convective Mach number 1.24.
在对流马赫数为1.24的超声速湍流混合层风洞中，以NPLS实验技术为基础观察到了小激波结构。
The shocklet was observed based on NPLS techniques in supersonic turbulent mix layer wind tunnel with convective Mach number 1.24.
在对流马赫数为1.24的超声速湍流混合层风洞中，以NPLS实验技术为基础观察到了小激波结构。
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