无限翼展后掠翼大迎角绕流和涡控制的数值模拟  

Numerical Simulation on Viscous Flows and Vartex Control about an Infinite Span Untapered Swept-Wing

作　　者：舒桃[1] 陆夕云[1] 杨国伟[1] 庄礼贤[1] 

机构地区：[1]中国科学技术大学力学和机械工程系,合肥230026

出　　处：《空气动力学学报》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)

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.

关 键 词：后掠翼 涡控制 大迎角 绕流数值模拟 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]