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应用测压、测力、七孔管测速和激光流态显示等方法对三种(等弦长、分段、台阶)型式涡襟冀进行了实验研究,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,实验表明适当控制前端襟翼使分离涡不破裂,可使该布局同时具有减小阻力和增加升力的效果。
The three types of chord (slender, segmented, step) vortex lap jets were experimentally studied by means of manometry, force measurement, seven-hole tube velocity measurement and laser flow pattern display, and compared with the basic wing 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 front wing of the wing is made into a flap (front flap) and the rear flap is provided. The interference of the two front flaps on the vortex flaps is studied. Experiments show that proper control of the front flap makes the split vortex not rupture, This layout also has the effect of reducing the drag and increasing the lift.