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首页> 外文期刊>International Journal of Scientific & Technology Research >Study Of Unmanned Aerial Vehicle With Variation Of Dihedral Angle And Configuration Of Empennage Using Computational Fluid Dynamics Methods
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Study Of Unmanned Aerial Vehicle With Variation Of Dihedral Angle And Configuration Of Empennage Using Computational Fluid Dynamics Methods

机译：计算流体动力学方法研究二面角变化和尾翼构型的无人机

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Unmanned Aerial Vehicle is a type of aircraft that has a very wide application. In this study, numerical calculations were performed using ANSYS Fluent software to find the configuration and dihedral angles that were considered to provide the best lift, drag, and moment pitch values. The study was conducted by varying two-tail configurations with high and low specifications with each having three variations in the dihedral angle values. Each variation has the same stabilizer surface area value. The study was conducted using the k-omega SST turbulence model (k-ω SST) with the mission profile having a distance of 200 km, a height of 500 m, and a speed of 20.83 m/s. Mesh is made of polyhedral with quality skewness and mesh orthogonal very good. The results of this study indicate that unmanned aircraft with a low tail configuration with the smallest dihedral angle produces the biggest lift and pitch moment value. The drag value produced by each variation has a very small difference that can be ignored.
机译：无人飞行器是一种用途非常广泛的飞机。在这项研究中，使用ANSYS Fluent软件进行了数值计算，以找到被认为可以提供最佳升力，阻力和力矩俯仰值的构型和二面角。通过改变具有高和低规格的两个尾部配置来进行研究，每个配置具有三个不同的二面角值。每个变化具有相同的稳定剂表面积值。该研究是使用k-omega SST湍流模型（k-ωSST）进行的，任务剖面的距离为200 km，高度为500 m，速度为20.83 m / s。网格由多面体制成，具有良好的偏斜度，并且网格正交性非常好。这项研究的结果表明，具有低尾翼配置，二面角最小的无人飞机产生的升力和俯仰力矩值最大。每个变化产生的阻力值具有很小的差异，可以忽略不计。

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