Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on Isight
As one of the main development trends of the next generation rotor-crafts, it is of important significance to study the aerodynamic optimization design of its wings for improving the flight performance of tiltrotor aircraft.NACA2412 is employed as the benchmark airfoil.Firstly, the airfoil parameter...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | zho |
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Editorial Department of Advances in Aeronautical Science and Engineering
2019-08-01
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| Series: | Hangkong gongcheng jinzhan |
| Subjects: | |
| Online Access: | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2018089?st=article_issue |
| _version_ | 1798018874131611648 |
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| author | Zhao Guang He Guoyi Wang Qi Luo Yun Wang Zhen |
| author_facet | Zhao Guang He Guoyi Wang Qi Luo Yun Wang Zhen |
| author_sort | Zhao Guang |
| collection | DOAJ |
| description | As one of the main development trends of the next generation rotor-crafts, it is of important significance to study the aerodynamic optimization design of its wings for improving the flight performance of tiltrotor aircraft.NACA2412 is employed as the benchmark airfoil.Firstly, the airfoil parameterization is carried out by Hicks-Henne method and the design variables is determined; Secondly, the softwares of Isight, mesh generation and flow field solver are used to build airfoil automatic optimization platform; Then, a surrogate model based on optimal Latin hypercube design(Opt LHD)and radial basis function(RBF)is adopted, and multi-island genetic algorithm(MIGA)is used to optimize the airfoil; Finally, the optimized airfoil is used to generate wing and the aerodynamic characteristics are calculated.In the optimization process, the optimization results of the two boundary conditions are compared to prove the effectiveness of the optimization method; the rotor is replaced by actuator disk by way of momentum source method to reduce the computational complexity.The results show that the lift-drag ratio of the optimized wing increases by 66.03% in the forward flight state when the airfoil is optimized according to the inflow velocity distribution along the wing span. |
| first_indexed | 2024-04-11T16:31:22Z |
| format | Article |
| id | doaj.art-645f9484017b4887a7a2e775b90dadfa |
| institution | Directory Open Access Journal |
| issn | 1674-8190 |
| language | zho |
| last_indexed | 2024-04-11T16:31:22Z |
| publishDate | 2019-08-01 |
| publisher | Editorial Department of Advances in Aeronautical Science and Engineering |
| record_format | Article |
| series | Hangkong gongcheng jinzhan |
| spelling | doaj.art-645f9484017b4887a7a2e775b90dadfa2022-12-22T04:14:00ZzhoEditorial Department of Advances in Aeronautical Science and EngineeringHangkong gongcheng jinzhan1674-81902019-08-01104514520,53510.16615/j.cnki.1674-8190.2019.04.01120190411Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on IsightZhao Guang0He Guoyi1Wang Qi2Luo Yun3Wang Zhen4School of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, ChinaSchool of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, ChinaSchool of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, ChinaSchool of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, ChinaSchool of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, ChinaAs one of the main development trends of the next generation rotor-crafts, it is of important significance to study the aerodynamic optimization design of its wings for improving the flight performance of tiltrotor aircraft.NACA2412 is employed as the benchmark airfoil.Firstly, the airfoil parameterization is carried out by Hicks-Henne method and the design variables is determined; Secondly, the softwares of Isight, mesh generation and flow field solver are used to build airfoil automatic optimization platform; Then, a surrogate model based on optimal Latin hypercube design(Opt LHD)and radial basis function(RBF)is adopted, and multi-island genetic algorithm(MIGA)is used to optimize the airfoil; Finally, the optimized airfoil is used to generate wing and the aerodynamic characteristics are calculated.In the optimization process, the optimization results of the two boundary conditions are compared to prove the effectiveness of the optimization method; the rotor is replaced by actuator disk by way of momentum source method to reduce the computational complexity.The results show that the lift-drag ratio of the optimized wing increases by 66.03% in the forward flight state when the airfoil is optimized according to the inflow velocity distribution along the wing span.http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2018089?st=article_issuetiltrotor aircraftairfoil optimizationisightsurrogate modelmomentum source method |
| spellingShingle | Zhao Guang He Guoyi Wang Qi Luo Yun Wang Zhen Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on Isight Hangkong gongcheng jinzhan tiltrotor aircraft airfoil optimization isight surrogate model momentum source method |
| title | Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on Isight |
| title_full | Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on Isight |
| title_fullStr | Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on Isight |
| title_full_unstemmed | Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on Isight |
| title_short | Airfoil Optimization of Tiltrotor Aircraft Forward Flight Mode Based on Isight |
| title_sort | airfoil optimization of tiltrotor aircraft forward flight mode based on isight |
| topic | tiltrotor aircraft airfoil optimization isight surrogate model momentum source method |
| url | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2018089?st=article_issue |
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