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- Computer Database of Wind Tunnel Data 风洞模型计算机数据库
- Wind tunnel data acquire technology 风洞数据采集技术
- They provide a signal proportional to pressure which can be automatically recorded by the usual wind tunnel data system 它们给出的信号与压力成正比,这些信号可以用通常的风洞数据系统自动记录
- Wind Tunnel Data 风洞实验数据
- The planes survived the wind tunnel test intact. 这些纸飞机在测试风道中丝毫未损。
- 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。
- 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。
- 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。
- 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。
- A wind tunnel and data acquisition system for transient experiment are setup.HSV color space is used to interpret the color and to determine the color versus temperature relation. 建立了基于瞬态实验技术的风洞和测试系统,用HSV色彩模型对颜色进行描述,得到颜色-温度关系;
- Using wind tunnel test data, the company added new fenders, with built-in gills, to widen the car by 5cm, and modified the bumpers, side mirrors, side skirts, and steel mesh. 利用风洞试验数据,该公司增加了新的挡泥板,带有内置鳃,扩大汽车五厘米,并修改了保险杠,侧后视镜,侧裙,和钢丝网。;
- The measurements were carried out in the large-scale wind tunnel at low speed of 9 m/s.Presented data consists of profiles of mean velocity and Reynolds stresses. 实验结果表明,气流流出扩压叶栅出口后,吸力面和压力面的通道涡将在较长的距离内保持其形态和强度,但是尾迹的形成及尾迹在压力的作用下向吸力面方向的偏斜成为了这一阶段的主要流动现象。
- 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。
- 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。
- Based on the analysis of the differences between wind tunnel test and field measurements and the differences between numerical results and test data,some referential conclusions are drawn. 将数值预测的压力场与实测结果及缩尺模型风洞试验数据进行了比较;分析了风洞试验与场地实测之间、数值模拟与试验之间的异同;得到一些有参考价值的结果.
- 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。