With the development of flight technology, the need for stable aerodynamic and vibration performance of the aircraft in the civil and military fields has gradually increased. In this case, the requirements for aerodynamic and vibration characteristics of the aircraft have also been strengthened. The existing four-rotor aircraft carries limited airborne equipment and payload, while the current eight-rotor aircraft adopts a plane layout. The size of the propeller is generally fixed, including the load capacity. The upper and lower tower layout analyzed in this paper can effectively solve the problems of insufficient four-axis load and unstable aerodynamic and vibration performance of the existing eight-axis aircraft. This paper takes the miniature octorotor as the research object and studies the aerodynamic characteristics of the miniature octorotor at different low Reynolds numbers, different air pressures and thicknesses, and the lift coefficient and lift-to-drag ratio, as well as the vibration under different elastic moduli and air pressure characteristics. The research algorithm adopted in this paper is the numerical method of fluid-solid cohesion and the control equation of flow field analysis. The research results show that, with the increase in the Reynolds number within a certain range, the aerodynamic characteristics of the miniature octorotor gradually become better. When the elastic modulus is 2.5 E, the aircraft’s specific performance is that the lift increases, the critical angle of attack increases, the drag decreases, the lift-to-drag ratio increases significantly, and the angle of attack decreases. However, the transition position of the flow around the airfoil surface is getting closer to the leading edge, and its state is more likely to transition from laminar flow to turbulent flow. When the unidirectional carbon fiber-reinforced thickness is 0.2 mm and the thin arc-shaped airfoil with the convex structure has a uniform thickness of 2.5% and a uniform curvature of 4.5%, the aerodynamic and vibration characteristics of the octorotor aircraft are most beneficial to flight.

中文翻译：

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微型八轴飞行器低雷诺数下的气动和振动特性

随着飞行技术的发展，民用和军用领域对飞机稳定的气动和振动性能的需求逐渐增加。在这种情况下，对飞机气动和振动特性的要求也得到了加强。现有的四旋翼飞机携带的机载设备和载荷有限，而目前的八旋翼飞机采用平面布局。螺旋桨的尺寸一般是固定的，包括负载能力。本文分析的上下塔架布局可以有效解决现有八轴飞行器四轴载荷不足和气动振动性能不稳定的问题。本文以微型八旋翼为研究对象，研究了微型八旋翼在不同低雷诺数、不同气压和厚度下的气动特性、升力系数和升阻比，以及不同条件下的振动。弹性模量和气压特性。本文采用的研究算法是流固黏聚力数值方法和流场分析控制方程。研究结果表明，随着雷诺数在一定范围内的增加，微型八旋翼的气动特性逐渐变好。当弹性模量为2.5E时，飞机的具体性能是升力增加，临界迎角增加，阻力减小，升阻比显着增加，攻角减小。然而，翼型表面周围流动的过渡位置越来越靠近前缘，其状态更容易从层流过渡到湍流。当单向碳纤维增强厚度为 0.2 mm 且具有凸结构的薄弧形翼型厚度均匀为 2.5% 和曲率均匀为 4.5% 时，八旋翼飞机的气动和振动特性最有利于航班。