Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configuration
Based on the application requirements of a small hand-launched solar-powered unmanned aerial vehicle (UAV) in flying wing configuration, the optimization design of the low Reynolds number (LRN) reflexed airfoil is carried out in this study to meet several requirements such as high lift, mild stall,...
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| Format: | Article |
| Language: | zho |
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EDP Sciences
2022-06-01
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| Series: | Xibei Gongye Daxue Xuebao |
| Subjects: | |
| Online Access: | https://www.jnwpu.org/articles/jnwpu/full_html/2022/03/jnwpu2022403p512/jnwpu2022403p512.html |
| _version_ | 1797642170426982400 |
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| author | WANG Kelei ZHOU Zhou GUO Jiahao XU De |
| author_facet | WANG Kelei ZHOU Zhou GUO Jiahao XU De |
| author_sort | WANG Kelei |
| collection | DOAJ |
| description | Based on the application requirements of a small hand-launched solar-powered unmanned aerial vehicle (UAV) in flying wing configuration, the optimization design of the low Reynolds number (LRN) reflexed airfoil is carried out in this study to meet several requirements such as high lift, mild stall, demanding pitching moment. Firstly, the accuracy and reliability of both quasi-steady and unsteady numerical methods to simulate the LRN transition flow and the stall separated flow at large angles of attack (AOA) are validated by an airfoil case study at specified Reynolds numbers; Secondly, the LRN reflexed air-foil optimization design framework is established by using the CST parameterization method, the multi-island genetic algorithm (MIGA), and the kriging surrogate model; Lastly, the LRN reflexed airfoil optimization study is conducted by using the NACA 8-H-12 reflexed airfoil as the baseline airfoil, it shows that both the lift-to-drag performance and the stall characteristics of the designed airfoil is significantly improved when compared with the baseline airfoil, which are quite beneficial for the small hand-launched solar-powered UAV in flying wing configuration to realize the hand-launched take off and the high-lift long-endurance flight. |
| first_indexed | 2024-03-11T13:56:20Z |
| format | Article |
| id | doaj.art-8d89d94f46244ad18c5388a013802532 |
| institution | Directory Open Access Journal |
| issn | 1000-2758 2609-7125 |
| language | zho |
| last_indexed | 2024-03-11T13:56:20Z |
| publishDate | 2022-06-01 |
| publisher | EDP Sciences |
| record_format | Article |
| series | Xibei Gongye Daxue Xuebao |
| spelling | doaj.art-8d89d94f46244ad18c5388a0138025322023-11-02T06:43:57ZzhoEDP SciencesXibei Gongye Daxue Xuebao1000-27582609-71252022-06-0140351252310.1051/jnwpu/20224030512jnwpu2022403p512Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configurationWANG Kelei0ZHOU Zhou1GUO Jiahao2XU De3School of Aeronautics, Northwestern Polytechnical UniversitySchool of Aeronautics, Northwestern Polytechnical UniversitySchool of Aeronautics, Northwestern Polytechnical UniversitySchool of Aeronautics, Northwestern Polytechnical UniversityBased on the application requirements of a small hand-launched solar-powered unmanned aerial vehicle (UAV) in flying wing configuration, the optimization design of the low Reynolds number (LRN) reflexed airfoil is carried out in this study to meet several requirements such as high lift, mild stall, demanding pitching moment. Firstly, the accuracy and reliability of both quasi-steady and unsteady numerical methods to simulate the LRN transition flow and the stall separated flow at large angles of attack (AOA) are validated by an airfoil case study at specified Reynolds numbers; Secondly, the LRN reflexed air-foil optimization design framework is established by using the CST parameterization method, the multi-island genetic algorithm (MIGA), and the kriging surrogate model; Lastly, the LRN reflexed airfoil optimization study is conducted by using the NACA 8-H-12 reflexed airfoil as the baseline airfoil, it shows that both the lift-to-drag performance and the stall characteristics of the designed airfoil is significantly improved when compared with the baseline airfoil, which are quite beneficial for the small hand-launched solar-powered UAV in flying wing configuration to realize the hand-launched take off and the high-lift long-endurance flight.https://www.jnwpu.org/articles/jnwpu/full_html/2022/03/jnwpu2022403p512/jnwpu2022403p512.html飞翼布局太阳能无人机反弯翼型低雷诺数转捩流动大迎角失速分离流动优化设计 |
| spellingShingle | WANG Kelei ZHOU Zhou GUO Jiahao XU De Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configuration Xibei Gongye Daxue Xuebao 飞翼布局太阳能无人机 反弯翼型 低雷诺数转捩流动 大迎角失速分离流动 优化设计 |
| title | Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configuration |
| title_full | Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configuration |
| title_fullStr | Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configuration |
| title_full_unstemmed | Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configuration |
| title_short | Study on design of low Reynolds number reflexed airfoil for solar-powered UAV in flying wing configuration |
| title_sort | study on design of low reynolds number reflexed airfoil for solar powered uav in flying wing configuration |
| topic | 飞翼布局太阳能无人机 反弯翼型 低雷诺数转捩流动 大迎角失速分离流动 优化设计 |
| url | https://www.jnwpu.org/articles/jnwpu/full_html/2022/03/jnwpu2022403p512/jnwpu2022403p512.html |
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