某型加油机尾流特性试验研究

The experimental study for wake characteristic of the refueling airplane model

为了揭示加油机加油装置尾部流场的发展规律和加油机各部件对尾流区的干扰机理,很有必要精确测量尾流区不同截面的流动参数,研究尾流对加油装置的影响。介绍了在4m×3m风洞应用该风洞配备的空间流态测量与显示系统,对某型加油机加油装置尾部流场多个截面的流动参数进行了测量,并对其尾流特性进行研究。研究结果表明,当加油舱的安装角=1.5°时,油舱涡量最小;在挂架上装涡流发生器后,油舱涡的强度稍有减弱;尾流区的空间流场测量与显示有助于对加油机加油装置尾部流场发展规律的研究。

In order to reveal the developing law of refueling equipment of the refueling airplane and the interference on different components of plane, It is necessary to accurately measure different crosssection flow parameters in the tailstream region and to study the influence on refueling equipment. In the paper, Spatial flow visualization system equipped in 4m×3m wind tunnel is introduced. It is also described to measure several crosssection flow parameters in tailstream region of the refueling equipment and to study the wake characteristic. The study results is following: the vortex quantity of refueling cabin is the least when the fix angle of refueling cabin is 1.5 degree, the intensity of the dipstick's vortex weakens when installed vortex generator on the hook, and spatial flow visualization on tailstream region is very helpful to reveal the developing law of tailstream