典型布局无人机 (unmanned aerial vehicle, UAV) 作为模型飞行试验的研究载体, 研究其流场和气动性能至关重要. 旨在分析典型布局无人机在马赫数 Ma = 0.2、雷诺数 Re = 4.3 × 106 流动条件下的气动特性, 重点考察攻角 (angle of attack, AoA) 变化对无人机升阻比、表面压力分布及流场结构的影响. 采用高精度数值模拟方法, 系统评估了不同攻角下的飞行性能. 研究结果显示, 攻角约为 3 ◦ 时, 无人机可实现最优升阻特性, 且随着攻角的增大, 在机翼表面会呈现 λ 型流线分布. 此外, 探讨了无人机在非定常大攻角工况下的涡结构演变, 揭示了涡结构与无人机气动特性的关系

As the research carrier of model flight test, it is very important to study the flow field and aerodynamic characteristics of typical unmanned aerial vehicle (UAV). The purpose of this paper is to deeply analyze the aerodynamic characteristics of typical layout UAV under the flow conditions of Mach number Ma = 0.2 and Reynolds number Re = 4.3 × 106 , focusing on the influence of angle of attack (AoA) on the lift-to-drag ratio, surface pressure distribution and flow field structure of UAV. The high-precision numerical simulation method is used to systematically evaluate the flight performance at different angles of attack. The results show that when the angle of attack is about 3◦ , the UAV can achieve the optimal lift-drag characteristics, and with the increase of the angle of attack, there will be a λ-type streamline distribution on the wing surface. In addition, the evolution of the vortex structure of the UAV under unsteady high angle of attack conditions is discussed in depth, and the relationship between the vortex structure and the aerodynamic characteristics of the UAV is revealed.