双尾撑倒V尾无人机气动特性及静稳定性计算分析

在双尾撑无人机上配置倒V 形尾翼，其夹角会影响全机的气动特性和静稳定性。提出一种双尾撑倒V形尾翼布局，采用数值方法与U 形尾翼布局进行对比分析；对倒V 形及U 形尾翼布局的计算模型进行校核和验证，分析两种布局在不同迎角和侧滑角下的纵向、横向和航向气动特性及静稳定性。结果表明：倒V 形尾翼可减小浸润面积，使全机升阻比提高2.2%，增大了尾翼失速迎角，但横向静稳定度明显下降；当尾翼夹角小于90°时，倒V 形尾翼能够增强全机横向稳定性，夹角增大也会使航向静稳定度略有降低，而纵向静稳定度有一定增强。

Aerodynamic and static stability computations and analysis of a twin-boom UAV with inverted V-tail

A twin-boom UAV with inverted V-tail is proposed and compared with the existing U-tail one by numerical method. Verification and validation were made on the computational model. Longitudinal, lateral, and directional aerodynamic characteristics and static stability of the two configurations are investigated and compared, with different angles of attack and sideslip angles. The results show that the inverted V-tail can reduce the wetted area, increase the lift drag ratio of the whole aircraft by 2.2%, and increase the stall angle of attack of the tail, but the lateral static stability decreases apparently. Flow fields comparison shows that there is a great difference between the normal force position of the inverted V-tail and that of the U-tail, which is the main reason for the decrease of lateral stability. It is found that when the included angle is less than 90 degrees, the tail can enhance the lateral stability of the aircraft.