摘要
栅格翼阻力大的缺点一直是需要解决的问题,前期研究显示,栅格翼翼面后掠能有效减小超声速阶段的波阻。本文采用数值计算的方法,对栅格翼前缘不同后掠方式、后掠角度及前缘后掠贴体型栅格翼进行了分析研究,数值结果显示栅格翼前缘后掠能有效减小波阻,其中栅格格间交接点为尖点的后掠方式减阻效果更好;栅格翼前缘后掠角度对其升力特性的影响较大,主要体现于对栅格内部气流壅塞现象的改善方面;和背风面为平面的栅格翼相比较,前缘后掠贴体型栅格翼的升阻特性表现更优。
It＇s important to solve the drag problem of grid fin. Former studies indicated that fin with swept angle could reduce the wave drag at supersonic speed. Different method of windward swept and differ- ent swept angle of grid fins were investigated by the method of CFD, including the curve leeward gird fin. Numerical simulation results showed that windward swept grid fin could reduce the wave drag obviously, and the method of gird intersection swept performed better, the windward swept angle influenced the lift charac- teristics of grid fin basically, showing different effect on flow chocking modification, and the curve leeward gird fin had better performance at lift-to-drag ratio.
出处
《空气动力学学报》
EI
CSCD
北大核心
2012年第5期628-633,639,共7页
Acta Aerodynamica Sinica
关键词
栅格翼
前缘后掠
后掠角
气流壅塞
gird fin
windward swept
swept angle
flow chocking
