Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State
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 identif...
| Main Authors: | , , , , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2020-01-01
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| Series: | Symmetry |
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| Online Access: | https://www.mdpi.com/2073-8994/12/2/196 |
| _version_ | 1798002430349148160 |
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| author | Hai Du Wenjie Kong Yan Wang Wenjing Liu Mingqi Huang Weiguo Zhang Min Tang |
| author_facet | Hai Du Wenjie Kong Yan Wang Wenjing Liu Mingqi Huang Weiguo Zhang Min Tang |
| author_sort | Hai Du |
| collection | DOAJ |
| description | 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, <i>Q</i> criterion, and <i>Ω</i> 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 <i>Ω</i> criterion method has a smaller deviation and can accurately identify the vortex core radius and vortex boundary. |
| first_indexed | 2024-04-11T11:52:08Z |
| format | Article |
| id | doaj.art-87a555a9612c41589a785465828b9187 |
| institution | Directory Open Access Journal |
| issn | 2073-8994 |
| language | English |
| last_indexed | 2024-04-11T11:52:08Z |
| publishDate | 2020-01-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Symmetry |
| spelling | doaj.art-87a555a9612c41589a785465828b91872022-12-22T04:25:17ZengMDPI AGSymmetry2073-89942020-01-0112219610.3390/sym12020196sym12020196Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering StateHai Du0Wenjie Kong1Yan Wang2Wenjing Liu3Mingqi Huang4Weiguo Zhang5Min Tang6School of Energy and Power Engineering, Xihua University, Chengdu 610039, ChinaSchool of Energy and Power Engineering, Xihua University, Chengdu 610039, ChinaSchool of Energy and Power Engineering, Xihua University, Chengdu 610039, ChinaSchool of Energy and Power Engineering, Xihua University, Chengdu 610039, ChinaRotor Aerodynamics Key Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaRotor Aerodynamics Key Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaRotor Aerodynamics Key Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaThe 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, <i>Q</i> criterion, and <i>Ω</i> 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 <i>Ω</i> criterion method has a smaller deviation and can accurately identify the vortex core radius and vortex boundary.https://www.mdpi.com/2073-8994/12/2/196rotorblade tip vortexpivvortexvortex identification |
| spellingShingle | Hai Du Wenjie Kong Yan Wang Wenjing Liu Mingqi Huang Weiguo Zhang Min Tang Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State Symmetry rotor blade tip vortex piv vortex vortex identification |
| title | Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State |
| title_full | Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State |
| title_fullStr | Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State |
| title_full_unstemmed | Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State |
| title_short | Research on Rotorcraft Blade Tip Vortex Identification and Motion Characteristics in Hovering State |
| title_sort | research on rotorcraft blade tip vortex identification and motion characteristics in hovering state |
| topic | rotor blade tip vortex piv vortex vortex identification |
| url | https://www.mdpi.com/2073-8994/12/2/196 |
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