Czyż Zbigniew, Karpiński Paweł, Stryczniewicz Wit
Aeronautics Faculty, Military University of Aviation, 08-521 Dęblin, Poland.
Department of Thermodynamics, Fluid Mechanics and Aviation Propulsion Systems, Faculty of Mechanical Engineering, Lublin University of Technology, 20-618 Lublin, Poland.
Sensors (Basel). 2020 Sep 27;20(19):5537. doi: 10.3390/s20195537.
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., = 0 m/s and = 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.
本文介绍了关于多旋翼飞机周围气流的研究结果。该研究包括使用粒子图像测速技术对速度场进行分析。基于在风洞中进行的测试，针对风洞内两种气流速度值（即0米/秒和12.5米/秒），确定了测试对象在几个攻角值下通过螺旋桨轴的垂直平面内的速度及其分量的分布。将速度值确定为所采用参考系统坐标的函数，从而能够定义水平螺旋桨和研究对象本身机身的影响范围。这些测试使得对通过水平旋翼的气流进行定量和定性分析成为可能。特别关注了气流和攻角对所获得的速度场分布的影响。
