摘要
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。
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.
出处
《空气动力学学报》
EI
CSCD
北大核心
2011年第5期640-644,663,共6页
Acta Aerodynamica Sinica
基金
装备预研基金(批准号:9140A13010608HK5703)
关键词
大型飞机后体
数值模拟
流动控制
涡流发生器
transport airplane aft-body
numerical simulation
flow control
vortex generator
