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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 proposed. The main principle is to design a part of the airfoil on the upper surface of the wing as a movable airfoil. When the aircraft enters the landing stage and the angle of attack is large, the movable airfoil is properly raised. When lifted, it forms a step, through which the steady vortices created in the step control the flow on the wing’s upper surface while, at the same time, opening the wing-mounted Gurney flap so as to simultaneously lift the wing for lift and stall The purpose of the angle of attack, the method is more suitable for improving the landing performance of small aircraft or UAVs. By applying the method on a small aircraft, the numerical simulation results show that the maximum allowable lift coefficient of the wing is increased by 33% and the maximum allowable angle of attack is increased by 30%. In order to improve the landing performance of small aircraft to explore a promising method.