螺旋式翼梢小翼减阻技术研究  

The Study on the Spiroid Winglets Drag-reduction Technic

作　　者：吕飞[1] 陈迎春[2] 张彬乾[1] 李亚林[2] 王元元[1] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]上海飞机设计研究所,上海200232

出　　处：《机械科学与技术》2012年第1期15-18,共4页Mechanical Science and Technology for Aerospace Engineering

摘　　要：以减小诱导阻力为目标,以DLR-F4机翼为基本机翼,自行设计了两种外形的螺旋式翼梢小翼,采用CFD方法研究螺旋式翼梢小翼减阻的能力和流动机理。研究结果表明:螺旋式翼梢小翼具有显著的减阻增升能力,升力系数最大增量可达到12%以上,诱导阻力效率因子提高了37.5%。螺旋式翼梢小翼通过有效阻止翼梢集中涡的形成,减小诱导阻力,是一种很有发展前景的翼梢减阻技术。In this paper,taking DLR-F4 wing as a base wing,two types of spiroid winglets have been designed to decrease the induced drag.The drag-reduction capability and flow mechanism of spiroid winglets has been simulated by CFD method which is based on N-S equations.The results show that the spiroid winglets have much potential in the aspect of reducing induced drag and enhancing lift.The spiroid winglets can raise the lift coefficient by 12% and the span efficiency factor by 37.5% comparing with the initial geometry without winglets.The spiroid winglets reduce the induced drag by preventing the concentrated wingtip vortex from bringing effectively,it is a promising wingtip drag-reduction technic,which is worthy of further study.

关 键 词：螺旋式翼梢小翼 诱导阻力 翼梢涡 流动机理 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]