摘要
通过数值求解Navier Stokes方程 ,研究了无限翼展直后掠翼在不同后掠角下的大迎角粘性分离流 ,探讨了后掠角对流场结构和升阻力特性的影响。基于对流动特性的机理分析 ,文中进一步数值模拟了无限展长后掠翼带表面吹吸气的大迎角绕流 ,研究了以非定常质量引射作为外激发手段对后掠翼前缘涡形成、发展和脱泻 。
Viscous flows around an infinite span untapered swept back wing at high angles of attack are investigated numerically by solving the quasi two dimensional Navier Stokes equations to deal with the effects of the swept-angle on the flow structure and force behavior. Based on our calculated results, it is found that increasing the swept back angle can effectively delay flow stall and increase the nonlinear lift. Further more, a vortex control by means of a periodical mass injection/suction at the upper surface near the leading edge of the airfoil is performed to study the effects of the external forcing on the vortex formation, evolution and shedding as well as on the force behavior. It is proved that the forcing with the half frequency of nature vortex shedding is the most effective way to enhance the vortex lift in the low speed conditions.
出处
《空气动力学学报》
CSCD
北大核心
2000年第3期264-271,共8页
Acta Aerodynamica Sinica
基金
国家自然科学基金资助项目! (No .1 980 2 0 1 8)
关键词
后掠翼
涡控制
大迎角
绕流数值模拟
untapered sweep wing
vortex control
high angles of attack
numerical simulation
