摘要
本文应用染色液流动显示技术对后缘偏转喷流情况下 76°/4 0°双三角翼前缘涡破裂位置的变化进行了观测 ,实验结果表明偏转喷流主要推迟与喷流方向相同一侧前缘涡的破裂 ,而使另一侧前缘涡破裂略有提前 .随着喷流偏转角度的增大 ,喷流使两前缘涡破裂位置差逐渐增大 .另外 ,随着模型攻角的增大 ,前缘涡涡核与双三角翼翼面的夹角逐渐增大 。
Dye-injection flow visualization technique is used to observe the leading-edge vortex breakdown of a double delta wing with the leading-edge vectored jets. It is found that the vectored jet may delay the leading-edge vortex breakdown in the jet direction, and makes the other leading edge vortex breaking down somewhat early, besides, the difference in the two leading-edge vortex breakdown positions increases with the jet angle. It is also found that with the increase of the angle of attack, the angle between the double delta wing surface and the leading-edge vortex increases, which leads to the action of vectored jets on the vortex breakdown weakened.
出处
《实验力学》
CSCD
北大核心
2001年第4期372-377,共6页
Journal of Experimental Mechanics
基金
国家教育部高等院校博士学科点基金资助项目的部分成果 (项目编号 :971 3)
