边条翼前缘涡非定常涡场特性研究中PIV技术的应用  

Application of PIV technique in unsteady characteristics research of streak wing leading vortex

作　　者：吕志咏[1] 祝立国[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《流体力学实验与测量》2003年第2期15-18,共4页Experiments and Measurements in Fluid Mechanics

基　　金：航空基金项目(01A51041)

摘　　要：描述了应用PIV技术在水槽中对边条机翼上旋涡及破裂旋涡流场进行的测量和分析。实验是在北航水槽中进行的。通过PIV技术的测量,揭示了旋涡及破裂旋涡中的非定常特性,这种非定常特性同飞机上机翼、尾翼的抖振密切相关。实验结果表明,对于未破裂的边条涡,存在着两种非定常特性,其一是剪切层中不断地有小涡沿剪切层输运和合并。其二是由一次涡诱导的二次涡与剪切层中的小涡互相诱导引起的非定常现象。对于破裂涡,则发现与未破裂的涡相比,截面上涡量分布的区域突然扩大很多,最大涡量的绝对值也比上游未破裂区截面上的涡量最大值小。此外还发现在涡量分布区域出现反涡量,这同涡破裂后出现涡核螺旋变形有关。对于同一截面处涡量分布是非定常的。In this paper measurement result and analysis concerned with vortex flow and bursting vortex flow over a strake-wing are presented. The experiment was conducted at the water channel of BUAA. PIV technique was applied in the test to obtain unsteady velocity and vorticity field cross sections perpendicular to the water tunnel axis, which are concerned with buffet characteristics caused on wings and fins of a fighter. The test result shows that there are two kinds of unsteady phenomenon for vortex system over the strake-wing: firstly small vortices are shedding along shear layer separated from the strake-wing leading edge and merging. Secondly interaction between second vortex induced by the primary vortex and the small vortices causes unsteady phenomenon. Compared with the vortex flow, the zone of vorticity distribution over the section of a bursting vortex is more larger. The maximum vorticity value in the section is less than that in the upstream section where the vortex does not breakdown. Besides that there is counter vorticity in a sense in the section cross the bursting vortex which is due to spiral transformation of the bursting vortex core. Meanwhile the vorticity distribution over the section is changed with time.

关 键 词：边条翼 前缘涡 非定常特性 PIV技术 涡量场 机翼 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]