尖顶襟翼对70°三角翼前缘涡破裂的影响  

Effect of the apex flap on the leading edge vortex breakdownover a 70° delta wing

作　　者：徐燕[1] 王晋军[1] 李亚臣[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《流体力学实验与测量》2002年第2期52-56,共5页Experiments and Measurements in Fluid Mechanics

基　　金：国防科技预先研究基金资助项目

摘　　要：为了提高大迎角下三角翼的机动性,在北航0.6m×0.6m×4.0m水槽中对后掠角Λ为70°的三角翼模型进行流动显示实验来研究尖顶襟翼对三角翼前缘涡破裂的影响。迎角α范围为30°～50°,弯折位置为30%c,向下弯折角B为0°～30°。试验结果表明:低头的尖顶襟翼对延迟三角翼前缘涡的破裂有显著效果,且弯折位置在涡破裂点附近时,推迟涡破裂的效果较好。迎角α≤40°时,存在一个推迟前缘涡破裂最有效的弯折角度。对于迎角α=40°,当弯折角度B=20°时效果最佳,可使前缘涡涡破裂点位置推迟33%～35%c。The experiment was conducted to examine the effect of an apex flap on vortex breakdown position. Flow visualization techniques has been used to determine the position of the vortex breakdown over a 70°sweep angle delta wing in the water tunnel of crosssection 0.6m×0.6m. The range of attack angles was from 20° to 50°, and the delta wing can be deflected at 30% of its root chord, the flap angles varied from 0°to 30°.The results revealed that a drooping apex flap can delay vortex breakdown effectively, and the optimum design was at the position where the vortex breakdown occured.When α≤40°,there exited an optimum deflection angle at which the maximum delay of the vortex breakdown occurred, and the value of 33%～35%c was obtained at α=40°and B=20°.

关 键 词：尖顶襟翼 三角翼 前缘涡破裂 影响 流动显示 大迎角 分流 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]