一种新型大小机翼气动布局及气动特性研究

A Study of the Aerodynamic Layout and Aerodynamic Characteristics of a New Type of Large and Small Wings

飞行颠簸是大气湍流漩涡引起飞行器升力显著变化从而导致飞行不稳定的现象,针对这一问题,文章提出一种新型的可转动大小机翼布局形式,通过建立力学模型介绍应对飞行颠簸的原理,利用数值模拟的方法,围绕大小机翼弦长比、间隔、交错方式、翼差角等几何因素对该新型布局气动特性影响进行研究。结果表明大小机翼布局形式在大攻角、小间距时能抑制大机翼后缘处的流动分离上提高大机翼的气动效率,巡航攻角下有翼差角会使整体升阻比降低,交错靠近后缘整体气动性能较好,在优化的几何参数下,小机翼能够使大机翼升阻比提高34.84%,同时整体升阻比相较于无干扰升阻比仅降低3.78%,同时该布局可以使得飞行器离地速度最大降低13%,也在亚声速可压缩流动中有一定的适用性。

Flight bump is a significant change in lift caused by atmospheric turbulence vortex,which leads to flight instability.This paper proposes a new type of rotatable large and small wing layout,introduces its principle by establishing a mechanical model,and investigates the influence of geometric factors such as chord length ratio,spacing,staggering mode and wing differential angle on the aerodynamic characteristics of the new layout by using numerical simulation.The results show that at high angle of attack and small spacing,the large and small wing configuration can restrain the flow separation at the trailing edge of the large wing and improve the aerodynamic efficiency of the large wing;at the cruising angle of attack,the difference angle of the wing will reduce the overall lift-drag ratio;near the trailing edge,the overall aerodynamic performance is better;given the optimized geometric parameters,the small wing can increase the lift-to-drag ratio of the large wing by 34.84%,while the overall lift-to-drag ratio compared to the undisturbed lift-to-drag ratio is only 3.78%lower than the non-interference lift-to-drag ratio;and this layout can reduce the aircraft ground speed by up to 13%,which is applicable in subsonic compressible flow.