摘要
提出了一种新型气动方法,主要原理是通过将机翼上表面的一部分翼面设计为活动翼面,当飞机进入降落阶段、迎角较大时,适当抬高该活动翼面,在该翼面抬起后,形成一个台阶,通过台阶中产生的稳定驻涡来控制机翼上表面的流动,与此同时,打开安装在机翼上的Gurney襟翼,从而达到同时提高机翼升力和失速迎角的目的,该方法比较适合提高小型飞机或无人机的着陆性能。通过将该方法在某小型飞机上运用,数值模拟的结果表明:机翼的最大允许使用升力系数提高了33%,最大的允许使用迎角提高了30%。为提高小型飞机的着落性能探索出一种具有发展潜力的方法。
A new aerodynamic method is presented. The main principle is to design a movable part on the upper surface of the wing of an aircraft. When the aircraft access to the relatively larger angle of attack in the period of landing, a step can be formed by appropriately raising the downstream tip of the movable part, thus a stable trapped vortex is generated to control the flow above the upper surface of the wing. At the same time, the Gurney flap installed at the trailing-edge of the wing is operated. Both effects of enlarging the lift and the stall angle of attack will be achieved. The method will be very useful for small aircrafts or UAV configuration in improving their landing behavior. By the numerical simulation of given aircraft configuration, it is shown that the airfoil＇s maximum usable lift coefficient can be increased by 33%, and the stall angle of attack can be increased by 30%. It is believed to be a promising method to improve aircraft landing performance for the small aircrafts.
出处
《工程力学》
EI
CSCD
北大核心
2013年第5期287-292,304,共7页
Engineering Mechanics
基金
国家自然科学基金项目(11072199)
关键词
増升装置
分离涡
大迎角
失速
数值模拟
high lift device
separated vortex
high angle of attack
stall
numerical simulation
