双尾撑倒V尾无人机气动特性及静稳定性计算分析

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

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。

The inverted V-tail is equipped in a twin-boom UAV,whose intersection angle can influence the aerodynamic characteristics and static stability.A twin-boom UAV with inverted V-tail is proposed,and compared with the U-tail configuration by numerical method.The computational models of inverted V-tail and U-tail configuration are examined and verified numerically.The longitudinal,lateral and directional aerodynamic characteristics and static stability of the two configurations are investigated and compared at different angles of attack and side-slip 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,whereas the lateral static stability is decreased apparently.When the included angle is less than 90°,the tail can enhance the lateral stability of the aircraft.The increment of included angle leads to a slight decrement of directional stability,but makes certain increment of longitudinal stability.