摘要
为了抑制三角翼前缘涡破裂的发生 ,研究了大攻角下 ( 30°～ 5 0°)尖顶襟翼对 70°三角翼前缘涡破裂的影响 .在静态实验情况下 ,尖顶弯折对三角翼前缘涡破裂影响的参数有 2个 :尖顶襟翼弯折的角度及其长度 .染色液流态显示结果表明 :尖顶襟翼的向下弯折减小了靠近襟翼翼面的有效攻角 ,从而推迟了前缘涡破裂的发生 ,涡破裂位置随弯折角的变化呈非线性变化且弯折襟翼越长效果越好 ,α =35°时两个弯折组合的效果要比单个弯折的好 .
The effectiveness of the apex flaps to control the vortex breakdown on a 70° sweep angle delta wings was studied experimentally. The angle of attack was in a range of 30°～50°. The flap angles and its length were found to be two important factors in determining the position of vortex breakdown in steady flow. Flow visualization results reveal that a drooping apex flap, effectively lowering the angle of attack of the portion of the wing closest to the apex can delay vortex breakdown. The variation in the flap angle produces a nonlinear effect on the vortex breakdown location, and it can be seen that the biggest flap produces the most significant effectiveness. The effect of the combination of the two apex flaps is better than that of single flap at α =35°.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2002年第5期543-546,共4页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家部委基金资助项目
关键词
三角翼
尖顶襟翼
绕流
旋涡
战斗机
delta wings
flow visualization
experiment
apex flap
vortex breakdown
