1·The mass ratio and free stream turbulence have attained to considerably good level.
引射效率和气流的湍流度也达到相当好的水平。
2·Angle of ATTACK, the Angle of the wing chord in relation to the free stream airflow as it moves forward through the air.
迎角，机翼翼弦在空气中向前运动时与自由气流之间的夹角。
3·The results of dynamic pressure measurements show that pressure coefficients are increased when the free stream decelerated.
动态测压结果表明，在减速过程中，负压系数增大；
4·SAX sends back a free stream of events based on the XML constructs, and does not require data to be in memory except for the node currently being processed.
SAX根据XML构造发回一个自由的事件流，除了当前正被处理的节点外不要求其它数据在内存中。
5·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.
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。
6·For transonic free stream, sudden performance degradation occurs. For the further supersonic range, performance losses increase slightly with increasing Mach number.
在继续的超声速范围内，性能损失随外流马赫数增加只有小幅增长。
7·It is shown that aerospike nozzle performance losses caused by free stream primarily result from increase of lift body base drag and decrease of plug pressure distribution.
结果表明，外流造成的性能损失主要体现在运载器底部阻力增加和塞锥表面压强降低两方面。
8·During experiment, a directly connected wind tunnel was independently designed to simulate a free stream Mach at 5.3, based on which the dynamic process of inlet opening was studied;
实验中，自主设计了高超声速直联式风洞模拟自由来流马赫数5.3，通过测量进气道上壁面压力分布，研究了进气道开启过程的起动特性；
9·Hypersonic viscous interaction effects on measurement of free stream pressure in test section are studied through theoretical analysis, experiment measurement and numerical simulation.
通过理论分析、实验测量和数值模拟，研究高超声速粘性相互作用对实验段自由流静压测量的影响。
10·Both the ratio of friction velocity to free stream wind velocity and the thickness of airflow are subject to the sidewall effect, showing the increase trend with the decreasing aspect ratios.
随着风洞宽高比的减小，断面内中垂线上的气流摩阻速度与自由流速的比值以及受风洞边壁影响的气流厚度均增大。