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Open AccessArticle

Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State

1
School of Energy and Power Engineering, Xihua University, Chengdu 610039, China
2
Key Laboratory of Fluid and Power Machinery, Ministry of Education, Xihua University, Chengdu 610039, China
3
Rotor Aerodynamics Key Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, China
*
Author to whom correspondence should be addressed.
Symmetry 2020, 12(2), 196; https://doi.org/10.3390/sym12020196
Received: 26 December 2019 / Revised: 17 January 2020 / Accepted: 19 January 2020 / Published: 29 January 2020
(This article belongs to the Special Issue Fluid Mechanics Physical Problems and Symmetry)
The rotorcraft blade tip vortex rolled up by the blade tip when the rotor rotates at high speed will produce a complex induced velocity field, which will have an important impact on the aerodynamic load and performance of the rotor. For this reason, this paper carries out the research on the identification of blade tip vortex and the motion characteristics of the vortex. Through the time-resolved particle image velocimetry (TR-PIV) experiment, the flow field of the rotor at a fixed rotate speed (2100 r/min) with a collective pitch of 6° and 9° was obtained. Based on the vorticity field, Q criterion, and Ω criterion, the research on vortex identification and vortex motion characteristics are realized. The results show that with the increase of blade motion azimuth, the radial position of blade tip vortex gradually contracts inward and the axial position moves downward in hovering state. As the collective pitch of the rotor increases, the radial contraction becomes more obvious, and the axial displacement increases, at the same time, the blade tip vortex intensity increases. Comparative study results show that different vortex identification methods have obtained certain deviations in the vortex center. Compared with other vortex identification methods, the Ω criterion method has a smaller deviation and can accurately identify the vortex core radius and vortex boundary. View Full-Text
Keywords: rotor; blade tip vortex; PIV; vortex; vortex identification rotor; blade tip vortex; PIV; vortex; vortex identification
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MDPI and ACS Style

Du, H.; Kong, W.; Wang, Y.; Liu, W.; Huang, M.; Zhang, W.; Tang, M. Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State. Symmetry 2020, 12, 196.

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