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 order to reduce the induced resistance, DLR-F4 wings are used as the basic wings. Two types of spiral wingtips are designed by themselves. The CFD method is used to study the drag reduction ability and flow mechanism of spiral wingtips. . The results show that the spiral winglets have significant drag reduction and increase ability, the maximum increment of lift coefficient can reach more than 12%, and the inductive drag efficiency factor increases by 37.5%. The spiral winglet winglex is a very promising wing tip drag reduction technology by effectively preventing the formation of a concentrated vortex wing tip and reducing the induced resistance.