论文部分内容阅读
应用测压、测力、七孔管测速和激光片光源的流态显示等方法对三种(等弦长、分段、台阶)型式涡襟翼进行了实验研究,并和基本翼(74°后掠三角翼)作比较。发现单纯改变涡襟翼的形式和参数能提高减阻效果,但不能改变小迎角下升力过小的现象。为此将机翼前端作成襟翼形式(前端襟翼),并配置后缘襟翼,研究了两种前端襟翼对涡襟翼的干扰,实验证明在某些情况下干扰是有利的,适当控制前端襟翼使分离涡不破裂,可使布局具有减小阻力和增加升力的效果。
Three types of (vortex length, section, step) vortex flaps were experimentally studied by means of manometry, force measurement, seven-hole tube velocity measurement and the flow pattern display of laser light source. Swept delta wing) for comparison. It is found that simply changing the form and parameters of vortex flaps can improve the drag reduction effect, but can not change the phenomenon of too small lift force at small angle of attack. For this purpose, the leading edge of the wing is formed as a flap (front flap) and trailing edge flaps are provided. The interference of the two front flaps on the vortex flaps is studied. Experiments show that in some cases the interference is favorable, Control of the front flap allows the separation vortex does not rupture, the layout can reduce drag and increase lift effect.