大型飞机后体流动控制及减阻机理研究

摘要

In this paper, numerical simulation has been used to research the flow characteristics and mechanism of transport aircraft aft-body, vortex generators were used to control separated flows of aft-body, and it got an analysis of drag reduction mechanism by controlled, and also discussed the effect of different parameters on drag reduction. Calculation results show that; the drag of transport airplane aft-body is mainly caused by the flow separation of aft-body ; vortex generators were fixed on the bottom of aft-body, and reached a certain drag reduction in the negative angle of attack. Size, circumferential distance and the forward or after location on the body of vortex generator have a certain influence with the drag reduction results.%通过数值模拟方法研究了大型飞机机身后体的流动特征和机理,并采用涡流发生器对机身后体流动分离进行控制,分析了其控制减阻的机理,讨论了不同参数对减阻效率的影响.计算结果表明:大型飞机机身后体流动分离是导致巡航阻力增加的一个重要因素；在后体底部附近安装涡流发生器,当来流迎角为负时减阻效果较明显,随着迎角的逐渐增大,减阻效果降低；涡流发生器的尺寸、周向距离、安装在机身后体上的前后位置、安装角度等参数对减阻效果具有显著影响.