Gurney襟翼对某型客机流动控制数值模拟

Numerical Simulation of Flow Control over a Certain Aircraft with Gurney Flaps

为改善某型客机的起降性能,通过在机翼尾缘加装Gurney襟翼,对流场进行了数值模拟。对该客机机翼的控制翼型安装不同高度的Gurney襟翼进行数值模拟,结果表明安装Gurney襟翼可以提高多段翼型的升力系数和阻力系数,但会增强尾迹流动的不稳定性。将不同高度的Gurney襟翼应用于该客机的简化模型,机翼的大部分区域符合二维翼型研究得出的流动控制规律;在机翼外侧区域,Gurney襟翼使机翼附近流场中的翼尖涡发生了一定的变化。数值模拟的结果还表明,Gunney襟翼可以提高客机的升力系数,而且不会给飞机流场带来明显的改变。

Abstract ： This investigation is conducted to use Gurney flaps to improve the performance of an aircraft during taking off and landing. Numerical simulation method is used in the flow control study for a certain type of aircraft in the landing mode with Gurney flaps installed on the wing＇s trailing edge. The aircraft＇s main airfoil and the airfoils with Gurney flaps of different heights are simulated. The result indicates that the Gurney flap could improve the lift coefficient and drag coefficient of the multi-element airfoil, but it also enhances the flow instability. A simplified model of the aircraft and the models with Gurney flaps of different heights are simulated. In most of the wing region, the models with Gurney flaps show a flow pattern that ac- corded with the two-dimensional airfoil models with Gurney flaps, but in the outer region of the wing, Gurney flaps cause the tip vortex near the wing flow field to exert a greater impact. Numerical results show that Gurney flaps efficiently improve lift coefficient of the aircraft without significant changes to the flow field.