前缘缝翼

多段翼型前缘缝翼位置的优化设计研究

Optimum Design of Multielement Airfoil Slat - Position for Maximum Lift

为了研究高升力系统中开口分段的前缘缝翼对增升装置气动特性的影响，对不同构型生成结构化网格，及其流场进行了大量的数值模拟。

In order to get the influence of split slat on wing ′ s aerodynamics , use the structuring grid to simulate the low speed viscous complex flow around the different split slat .

以最大升力系数为目标函数，对前缘缝翼或襟翼的位置和偏角进行优化。

We take the maximum lift coefficient as the objective function .

研究表明，机翼失速不仅与开口宽度有关，而且与前缘缝翼上的开口位置有关。

The research shows that the stall of wing is not only related with the split distance but also with the position of the split .

前缘缝翼优化时，用主翼面上的分离点位置作为间接目标函数；

For the optimization of a leading-edge slot , the separating position of the main element is used as indirect target function for optimizing caculation ;

一种带前缘襟翼或缝翼的机翼的跨声速试验

Transonic test for a wing with leading edge fiap or slat