GAW-1翼型前后缘变弯度气动性能研究

传统增升装置主要用于提高飞机起降气动性能。利用计算流体力学(CFD)的方法,引入了通用飞机翼型的前后缘变弯装置的概念,数值模拟了GAW-1翼型在爬升状态时,前缘变弯装置、后缘襟翼/副翼偏转以及前后缘装置综合偏转对翼型气动特性的影响。研究表明,前缘变弯装置可以有效地改善翼型的失速特性,失速迎角提高了3°左右,最大升力系数提高了4.56%;同时提高升阻比50%~120%;但在设计升力系数下,升力系数和阻力系数都略微减小。另一方面,后缘变弯装置可以改变最大升阻比所对应的迎角,以及在小迎角时,提高升力系数6%左右。翼型综合偏转可以在小迎角时增加升力系数,在大迎角时增加升阻比。

Aerodynamic performance of GAW-1 airfoil leading-edge and trailing-edge variable camber

The traditional high-lift device is used to improve the taking-off and landing aerodynamic performance of aircraft. By using the method of computational fluid dynamics(CFD), an idea of leading-edge and trailing-edge variable camber devices based on general aviation airfoil is introduced. The influences of leading-edge variable camber device, trailing-edge flap/aileron, and both leading-edge and trailing-edge variable camber devices of GAW-1 airfoil in the climbing state on airfoil aerodynamic performances are studied respectively. Learning from the results, leading-edge variable camber device can effectively improve the airfoil stall characteristics, increasing the angle of stall by about 3°, and the maximum lift coefficient has been increased by 4.56%. At the same time, the lift-to-drag ratio has been increased by 50% to 120%. But with the design lift coefficient, both lift coefficient and drag coefficient have been decreased. On the other hand, the function of trailing-edge variable camber device is to reposition the maximum of lift-to-drag ratio and to increase the lift coefficient by about 6% at a small angle of attack. Composite deflection of airfoil can increase lift coefficient at small angle of attack and increase lift-to-drag ratio at large angle of attack.