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- free jet wind tunnel 工孜敞开式风洞,自由喷射风洞
- closed jet wind tunnel 闭口式风洞
- open jet wind tunnel 开口式风洞,工孜敞开式风洞
- 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。
- After the study, further recongniztion are done to flow characteristics of high enthalpy free piston shock wave wind tunnel. 通过该研究工作,对高焓自由活塞激波风洞的流动特性有进一步的认识。
- Our wind tunnel free flight experiment results show that this kind of shape when M=5 generates conical destabilization,and its occurrence rate reaches 100%. 但是简单尖锥体、小钝锥体我们的风洞自由飞实验结果(M=5):会产生锥动失稳,甚至实验次数中出现锥动失稳的比例达100%25。
- 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。
- Based on sandblast working principle and structure characters of blast gun, free jet model was developed in eject sect. 根据喷砂工作原理和喷枪结构特征建立了引射段的自由射流模型。
- In there it forms an aerated cavity between the step surface and the free jet to improve aerification. 通过数值模拟得到的墩后水翅、阶梯面挑射水舌和掺气腔体等,与实验观测到的现象吻合。
- About the experiment, these experiments were conducted in the free stream wind tunnel, and vitiated air heater was used to simulate the high altitude flow condition. 试验方面:本文试验在自由射流风洞中进行,利用空气加热器模拟高空飞行条件。
- Based on sandblast working principle and structural characters of blast gun, free jet model was developed in eject sect. 根据喷砂工作原理和喷枪结构特征建立了引射段的自由射流模型。
- 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 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。
- The distributions of velocity, pressure, temperature, supersaturation and nucleation rate of supercritical solution in entrance of the nozzle, inside of the nozzle and the free jet were simulated... 模拟了超临界溶液在喷嘴入口段、喷嘴以及喷嘴后自由喷射段中的流速、压力、温度、过饱和度以及成核速率的分布。
- 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。
- 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。
- 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。