民机不同后体空间流态水洞实验研究  

The flow visualization of the different afterbody of the airliner

作　　者：张华[1] 刘昌[1] 秦燕华[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系,北京100083

出　　处：《水动力学研究与进展（A辑）》2004年第5期616-622,共7页Chinese Journal of Hydrodynamics

摘　　要：　利用荧光黄纳及片光在水槽中对具有不同收缩比的民机后体的复杂绕流进行流动显示,探讨了后体的分离尾涡特性及参数影响,实验发现后体收缩比改变时对应了两种典型的尾涡流态,即稳定流向尾涡和周期性尾涡,并进一步探讨了尾翼对后体尾涡的影响。The flow visualization of different afterbodies of airliner is undertaken with the fluorescence and the laser light sheet method in the water channel of BUAA. The separation and wake vortex characteristics are discussed. It is shown that there are two different types of wake vortex, the stable wake vortex and the periodically shedding wake vortex-chain, as the contract ratio of afterbody changes. The influence of the tail wing on the separation and the wake vortex are also discussed.

关 键 词：民机 后体 流动显示 分离 旋涡 

分 类 号：TV131[水利工程—水力学及河流动力学]