后掠机翼低速流动转捩位置的升华法测量  

Measurement of Transition Location Change of Swept Wing in a Low-Speed Flow Based on Sublimation Method

作　　者：王斌[1] 白存儒[1] 杨广郡[1] 杨永[1] 

机构地区：[1]西北工业大学,陕西西安710072

出　　处：《实验力学》2009年第3期197-201,共5页Journal of Experimental Mechanics

基　　金：西北工业大学科技创新基金重点项目"后掠机翼的附面层流动稳定性及层流控制"资助

摘　　要：报导了在西北工业大学低湍流度风洞中采用升华法测量后掠翼上表面流动转捩位置及其随攻角变化而改变情况,并参照后掠翼压力分布的实验结果进行分析。本文涉及的升华法,是根据边界层的层流区和湍流区流态差别来判断边界层转捩的一种测量方法。升华法的测量结果表明:在小攻角范围内,转捩位置逐渐提前,当达到某一攻角时,转捩快速接近前缘。这一结果和压力分布的实验结果相吻合,说明升华法能够较准确地显示转捩线位置。由于影响后掠翼转捩位置的因素较多,诸如边界层内横流的不稳定性、壁面的干扰、后掠翼的三维流动效应等,致使出现了攻角为4°时转捩位置呈现出一条斜线的现象。This paper reports the measurement of transition location change of NLF（2）-0415 swept wing in a low-speed flow along with the attack angle based on sublimation method in a low turbulence wind tunnel mounted at Northwestern Polytechnical University. Results were analyzed by comparison with the experimental data of pressure distribution on a swept wing. Sublimation method referred in this paper is a measurement method that judges the boundary layer transition based on the flow state difference between the laminar area and the turbulence area in a boundary layer. Measurement results indicate that the transition location is gradually close to the leading edge for small attack angles; the transition location is suddenly close to the leading edge when attack angle reaches a certain angle. This is consistent with the experimental results of pressure distribution and indicates that sublimation method can correctly display the transition location. Many factors may affect the transition location of a swept wing, such as the unsteadiness of crosscurrent in boundary layer, the disturbance from tunnel＇s wall, the three-dimensional flow effect of swept wing and so on, all above will result in the phenomenon that transition line appear a bias when the attack angle is 4 degree.

关 键 词：转捩 低湍流度风洞 升华法 自然层流机翼 后掠翼 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]