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- hypersonic pulsed wind tunnel 高超声速脉冲风洞
- 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。
- The design concept and principle of injector valve system of hypersonic wind tunnel controlled by the computer are introduced in this paper. 本文介绍了高超声速风洞引射器阀门系统采用计算机控制的设计思想和原理框图。
- The planes survived the wind tunnel test intact. 这些纸飞机在测试风道中丝毫未损。
- 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 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。
- Abstract: Model free flight experiments were carried out in impulse hypersonic wind tunnel at Institute of Mechanics, Chinese Academy of Sciences to obtain pitching damp of two space shuttle models. 文摘:采用模型自由飞技术在脉冲型高超声速风洞中测量了两种类航天飞机外形模型的俯仰阻尼导数。
- Aerodynamic characteristics of some hypersonic rockets are calculated and the results are compared with that of wind tunnel test to verify the reliability of the calculation method. 计算了某高超音速火箭的气动特性，并用风洞试验数据进行比较，验证了计算方法是可靠的。
- 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。
- 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。
- Hypersonic wind tunnels operating at very low densities were developed starting in about 1960. 低密度超音速风洞大约开始发展于1960年。
- 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。
- hypersonic wind tunnel experiment 高超声速风洞试验
- Ames Dimensional Hypersonic Wind Tunnel 埃姆斯量纲高超音速风洞
- 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。
- It puts emphasis on the devolopment of supersonic and hypersonic quiet wind tunnels technology at NASA Langley Research Center. 重点介绍了NASALangley研究中心的超声速、高超声速静风洞技术的发展。
- 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。
