This paper presents the results of research on the airflow around a multirotor aircraft. The research consisted of the analysis of the velocity field using particle image velocimetry. Based on the tests carried out in a wind tunnel, the distribution of the velocity and its components in the vertical plane passing through the propeller axis were determined for several values of the angle of attack of the tested object for two values of airflow velocity inside the tunnel, i.e., v_wt = 0 m/s and v_wt = 12.5 m/s. Determining the velocity value as a function of the coordinates of the adopted reference system allowed for defining the range of impact of the horizontal propellers and the fuselage of the research object itself. The tests allowed for quantitative and qualitative analyses of the airflow through the horizontal rotor. Particular attention was paid to the impact of the airflow and the angle of attack on the obtained velocity field distributions.

中文翻译：

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多旋翼螺旋桨流场测量


本文介绍了多旋翼飞行器周围气流的研究成果。该研究包括使用粒子图像测速技术分析速度场。根据在风洞中进行的试验，确定了在两个气流速度值下，测试对象的多个攻角值在通过螺旋桨轴的垂直平面内的速度及其分量的分布。隧道，即v _wt = 0 m/s， v _wt = 12.5 m/s。将速度值确定为所采用参考系坐标的函数，可以定义水平螺旋桨和研究对象本身机身的影响范围。这些测试可以对通过水平转子的气流进行定量和定性分析。特别注意气流和攻角对获得的速度场分布的影响。