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arc heated wind tunnel 弧加热风轮机
The planes survived the wind tunnel test intact. 这些纸飞机在测试风道中丝毫未损。
It is not correct to think of the wind tunnel having uniform flow. 设想风洞具有均匀的气流是不正确的。
The flow field visualization of a straight HP trubine cascade is conducted in alarge-scale low-speed open-loop cascade heat transfer wind tunnel. 在大尺寸低速叶栅传热风洞中对一种高压涡轮导向叶栅的流场进行了流动显示实验研究。
Setting very low speeds in a wind tunnel is always a vexatious problem. 在风洞中调出低风速来始终是一个麻烦问题。
To calculate the surface heat transfer rate of the experimentation model in wind tunnel,the isotherms should be extracted firstly from the phase change thermography sequences. 相变热图技术中,为了得到风洞试验模型表面的热流分布,必须对相变热图序列进行相变线提取。
We are developing a broad scale research in phase change thermography test technique in hypersonic wind tunnel,it s mainly used in a great heat transfer measurment. 高超声速风洞相变热图试验技术是我所正在开展研究的一项试验技术,主要应用于大面积热测量。
It should be noted that a balance is not always required in a wind tunnel. 应该指出，天平对风洞来说并非是绝对必须的。
The aerodynamics characteristics of this airfoil is studied in wind tunnel. 进行了翼型的低速气动力性能研究，为附面层特性研究提供了方向。结果表明，该翼型具有较好的升阻和俯仰特性，但失速特性差。
The hight voltage make use of a period of melting and a in front of middle period of oxidation time as soon as possible, we should make out scum and insure that electrical arc heat up in the scum. 高电压应尽可能在熔化期和氧化中前期使用,及早造好泡沫渣,确保电弧埋弧加热。
In the twodimensional wind tunnel, systematic experimental researches were carried out on the phenomenon of reverse transition on a heated plane with stable density stratification. 针对加热平板表面密度分层结构中的逆转捩现象,在二元风洞中进行了系统的实验研究。
The wind tunnel is produced under a technical cooperation agreement with Ford Co of US. 风洞机是根据与美国福特公司的技术合作协议生产的。
Any flight test and wind tunnel correlation always suffers from a great number of unknowns. 在对飞行试验与风洞试验进行比较时总有大量的未知数。
The experiments were conducted in a wind tunnel at a location 50 ft downwind from the fan. 实验是在风洞中距离风机50英尺处进行。
The damping derivatives can only be determined experimentally in the wind tunnel or ballistic range. 阻尼导数只能用风洞或弹道试验来确定。
In the experiment under the 20 m/s wind tunnel conditions, the wind abrasion modulus is almost zero. 在每秒20米的风洞实验中，吹蚀模数几乎为零。
In this paper, the initial stage in application of fuzzy logic to aircraft high-angle-of attack aerodynamics using wind tunnel test data is outlined. 本文概述最初阶段利用风洞试验数据应用模糊逻辑研究飞机大攻角空气动力学的情况。
In the experiment under the 20 m/s wind tunnel conditions,the wind abrasion modulus is almost zero. 在每秒20米的风洞实验中，吹蚀模数几乎为零。
Both types of tests have been explored in wind tunnels. 这两种形式的试验都已在风洞中进行过探索。
NASA and Boeing said data from the flight are already being compared with data from wind tunnel tests. NASA和波音公司的数据说,从飞行正在与风洞试验数据。