扇翼飞行器绕翼型流动数值研究

扇翼飞行器以其低速大载荷、低噪音特性在军用及民用领域有着广泛的应用前景．基于CFD软件采用滑移网格技术对简化为二维的绕翼型流动进行数值模拟，得到低速大迎角下绕翼型的流场，分析并比较了不同迎角下的流场结构，给出了升阻力随迎角的变化关系．在此基础上通过比对分析翼型局部几何形状改变后得到的数值模拟结果，得到了飞行器机翼前缘高度对绕翼型流场的影响以及相应的升阻力变化情况，并讨论了引起这些影响和变化的可能原因．最终给出可用于扇翼飞行器设计的方案．

Numerical study of flow over fan-wing airfoil

The fan-wing aircraft has a wide application prospect in military and civilian fields due to its characteristics of low speed, large load capacity, and low noise. Using the sliding mesh technology based on computational fluid dynamics （CFD）, the flow over the two-dimensional airfoil is simulated, under the condition of low-speed and high angle of attack. The flow features at different angles of attack are analyzed and compared, and the variation of lift and drag changing with the angle of attack is acquired. And on this basis, a numerical simulation was made on the fan-win which was modified locally in geometry. With the analysis and comparison, the effect of fan-wing leading edge height on the flow field around the airfoil is acquired, as well as the corresponding changes in lift and drag The possible reasons for such a significant effect are discussed. This paper is valuable for those working in the area of high-lift wing design.