摘要
该文通过风洞测力、油流和PIV流动显示测量实验,研究了涡流发生器对民机后体流动分离控制及减阻机理。实验结果表明:涡流发生器的高度、安装角度和安装位置是影响后体流动分离控制的主要参数,前缘后掠角度和长度等参数的影响相对较小;负迎角时在靠近机身尾部位置布置涡流发生器的减阻效率较高;较佳的涡流发生器控制方案中,后体分离的油流聚集线明显后移,同时空间PIV测得的分离涡量明显变小,从机理上印证了测力结果。
Control of separated flow over civil aircraft aft-body and drag reduction mechanism by using vortex generator have been presented by means of wind amnel force test, oil flow and PIV flow visualization test. It shows that the height, installation angle and fixed-location of vortex generator are the main parameters to separated flow over aft-body, while sweep angle and length of vortex generator have little effect. When vortex generator is installed at a negative attack angle, location near tail of fuselage proves energy-efficient to drag reduction. In a preferable control scheme of vortex generator, oil gather line in the separation area of aft-body is obviously deferred, and the separated eddy measured by PIV is obviously smaller, which validates the force test results.
出处
《工程力学》
EI
CSCD
北大核心
2012年第8期360-365,共6页
Engineering Mechanics
基金
大型飞机后体流动分离控制减阻应用技术研究(9140A13010608HK5703)
关键词
民机后体
流动控制
涡流发生器
风洞实验
流动显示
civil aircraft aft-body
flow control
vortex generator
wind tunnel test
flow visualization
