堑尾翼型的表面结构设计及其气动性能的仿真探究

DESIGN AND SIMULATION ON AERODYNAMIC PERFORMANCE OF SUNKEN TRAILING EDGE AIRFOIL

为解决传统翼型产生的边界层分离问题,提升机翼气动性能,本文基于NACA4412翼型提出了一种新翼型——堑尾翼,并在大量的仿真实验基础上证实,堑尾翼型具有比原翼型更优越的气动性能。本研究对不同形状、不同风速、不同攻角情形下堑尾翼型的升阻比增益倍数进行了系统讨论。研究数据表明,堑深为零、堑长约为翼型弦长1/3的堑尾翼型具有较优的气动性能,在中低速流场中堑尾翼最高可以得到1.6倍的升阻比增益倍数。因此,本研究可为中低速飞行器的翼型设计提供新的思路,在增大载荷的同时提高能源的利用率。

In the genre of aerospace,the transition of the boundary layer always seems to be a problem that limits the aerodynamic performance of a wing.Thus,an increasing number of experiments and researches are working on optimizing the airfoil to dilute the turbulence.Based on the NACA4412 airfoil,in this paper,a new type of airfoil,sunken trailing edge air-foil,is proposed and tested by means of the Flow Simulation unit of SOLIDWORKS.And it has been verified that the new airfoil has the superior aerodynamic performance compared to the original airfoil by a large number of simulation experiments.The lift drag ratio gain of the sunken trailing edge airfoil is systematically discussed with different shapes,wind speeds,and angles of attack.The research data show that when the sunk depth is around naught and the length is about one third of the chord,sunken trailing airfoil produces the greatest lift-drag ra-tio increase,which can be up to 60%more than the prototype's in mid-speed flow field.Thus,this study brings a new way to design an airfoil of medium and low speed aircraft,in-creasing load while improving energy utilization.