翼尖涡流场特性及其控制  

Flow field characteristics of wing tips vortex and its control

作　　者：顾蕴松[1] 程克明[1] 郑新军[1] 

机构地区：[1]南京航空航天大学空气动力学系,江苏南京210016

出　　处：《空气动力学学报》2008年第4期446-451,共6页Acta Aerodynamica Sinica

摘　　要：大型运输飞机的尾涡系是诱发后继小型飞机空难的重要原因,需要有效的涡控制装置来削弱其强度。通过风洞实验,研究了翼型为NACA23016的矩形半机翼模型翼尖尾涡流动结构和控制方法。应用七孔探针空间流场定量测试技术研究了翼尖涡的流动结构,给出了翼尖尾涡在下游两倍弦长距离内的速度和压力场分布随迎角变化的规律。在机翼翼梢布置不同组合方式的翼梢涡扩散器,来控制翼尖涡。研究结果表明,正负90°和60°安装角的双翼梢涡扩散器可将翼尖涡涡核的静压增加60%以上。其旋涡强度削弱机理为:翼梢涡扩散器将集中的翼尖涡破碎分成两个或多个强度更弱的旋涡。在流体粘性的作用下,旋涡能量耗散更快,可有效地削弱翼尖尾涡的强度。It is very dangerous for small airplane encountering the wake vortices flow of large transport aircraft. Specific vortex control device is need to decrease the vortices strengthen. The flow field of the wing tip vortex,which shed from a rectangular wing,is surveyed by a seven holes probe in a low speed wind tunnel. The features of wingtip vortex various with angle of attack of the wing and its development to two chord lengths down-stream from trailing edge are given. Some vortex diffusers are deployed at wing tip to control the vortex. The wing tips vortex is separated into two weaker vortices. The flow field measurement results show that the strength of wingtip-vortex can be obviously decreased with control of vortex diffusers.

关 键 词：翼尖涡 涡控制 翼梢涡扩散器 流场测量 七孔探针 

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]