螺旋桨滑流对不同尾翼无人机气动特性影响的对比分析

Comparative analysis on aerodynamic characteristics of the UAV with different tails under propeller slipstream

摘要:

长航时双尾撑布局无人机，通常将尾翼置于螺旋桨后，在这种情况下，螺旋桨滑流将严重影响全机的气动特性。针对基于倒U 尾/倒V 尾双尾撑布局无人机，采用数值计算方法对比分析螺旋桨滑流对两种布局无人机升阻特性、纵向静稳定性的影响。结果表明：双尾撑倒U 尾/倒V 尾无人机纵向静稳定度相近时，倒V 尾无人机尾容量较大；螺旋桨滑流影响下倒U 尾无人机阻力系数最大增加36.67%，倒V 尾无人机阻力系数最大增加35.21%，倒U 尾无人机升阻比减小4.14，倒V 尾无人机升阻比减小4.32，滑流对两种布局无人机升阻特性的影响大致相同；螺旋桨滑流影响下倒U 尾无人机纵向静稳定度减小2.09%，倒V 尾无人机纵向静稳定度减小0.99%，滑流影响下两种布局无人机纵向静稳定性均变差，其中，倒U 尾无人机纵向静稳定性恶化较严重。

Abstract:

The tails often placed behind the propeller of the long endurance twin-boom UAV. In this case, the propeller slipstream will affect the aerodynamic characteristics. Based on the twin-boom UAV with inverted U-tail and inverted V-tail, Comparative analysis on the lift-drag characteristic and longitudinal static stability of two type UAV under propeller slipstream by numerical calculation method. The results show that when the longitudinal static stability of inverted U-tail/inverted V-tail UAV is similar, the tail capacity of inverted V-tail UAV is larger. The maximum increase of inverted U-tail UAV’s drag coefficient is 36.67%, the maximum increase of inverted V-tail UAV’s drag coefficient is 35.12%, the lift-drag ratio of inverted U-tail UAV is reduced by 4.14, The lift-drag ratio of inverted V-tail UAV is reduced by 4.32 under propeller slipstream, The effect of two type UAV’s lift-drag characteristic under propeller slipstream are basically same. The longitudinal static stability of inverted U-tail UAV is decreases by 2.09%, The inverted V-tail UAV is decreases by 0.99% under propeller slipstream. The longitudinal static stability of two type UAV become worse under propeller slipstream, And the inverted U-tail UAV becomes worse seriously. It provides reference for the design of the long endurance UAV’s tail with two-boom.