Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept
As the novel active flow control technology,Co-flow Jet concept(CFJ)is one of the most potential methods to achieve the high lift enhancement and drag reduction of rotor airfoil.Based on the OA 312 rotor airfoil,the CFJ rotor airfoil dynamometric model driven by the micro ducted fan group is designe...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | zho |
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Editorial Department of Advances in Aeronautical Science and Engineering
2021-08-01
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| Series: | Hangkong gongcheng jinzhan |
| Subjects: | |
| Online Access: | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2021062?st=article_issue |
| _version_ | 1797955175896317952 |
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| author | ZHANG Shunlei YANG Xudong SONG Bifeng WANG Bo LI Zhuoyuan |
| author_facet | ZHANG Shunlei YANG Xudong SONG Bifeng WANG Bo LI Zhuoyuan |
| author_sort | ZHANG Shunlei |
| collection | DOAJ |
| description | As the novel active flow control technology,Co-flow Jet concept(CFJ)is one of the most potential methods to achieve the high lift enhancement and drag reduction of rotor airfoil.Based on the OA 312 rotor airfoil,the CFJ rotor airfoil dynamometric model driven by the micro ducted fan group is designed.The low-speed wind tunnel test of high lift enhancement and drag reduction of rotor airfoil using Co-flow Jet concept with zero mass and high negative pressure at the leading edge is conducted.The influence of basic parameters such as the injection size,suction size and suction surface translation on lift enhancement and drag reduction is studied.The optimal values of key parameters of CFJrotor airfoil are given.Results show that compared with the OA 312 baseline airfoil,the CFJ rotor airfoil can significantly reduce drag coefficients at low angle of attack,and even achieve“negative drag”while the zero-lift pitch moment is basically unchanged.The CFJ rotor airfoil can significantly increase the maximum lift coefficient and the stall angle of attack at high angle of attack.The maximum lift coefficient can be increased by about 67.5%,and the stall angle of attack is significantly delayed by nearly 14.8°. |
| first_indexed | 2024-04-10T23:29:04Z |
| format | Article |
| id | doaj.art-f7600d681eee444aa9622e0108b965ba |
| institution | Directory Open Access Journal |
| issn | 1674-8190 |
| language | zho |
| last_indexed | 2024-04-10T23:29:04Z |
| publishDate | 2021-08-01 |
| publisher | Editorial Department of Advances in Aeronautical Science and Engineering |
| record_format | Article |
| series | Hangkong gongcheng jinzhan |
| spelling | doaj.art-f7600d681eee444aa9622e0108b965ba2023-01-12T09:19:43ZzhoEditorial Department of Advances in Aeronautical Science and EngineeringHangkong gongcheng jinzhan1674-81902021-08-011244451,6710.16615/j.cnki.1674-8190.2021.04.052021045Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet ConceptZHANG Shunlei0YANG Xudong1SONG Bifeng2WANG Bo3LI Zhuoyuan4School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, ChinaSchool of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, ChinaSchool of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, ChinaSchool of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, ChinaSchool of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, ChinaAs the novel active flow control technology,Co-flow Jet concept(CFJ)is one of the most potential methods to achieve the high lift enhancement and drag reduction of rotor airfoil.Based on the OA 312 rotor airfoil,the CFJ rotor airfoil dynamometric model driven by the micro ducted fan group is designed.The low-speed wind tunnel test of high lift enhancement and drag reduction of rotor airfoil using Co-flow Jet concept with zero mass and high negative pressure at the leading edge is conducted.The influence of basic parameters such as the injection size,suction size and suction surface translation on lift enhancement and drag reduction is studied.The optimal values of key parameters of CFJrotor airfoil are given.Results show that compared with the OA 312 baseline airfoil,the CFJ rotor airfoil can significantly reduce drag coefficients at low angle of attack,and even achieve“negative drag”while the zero-lift pitch moment is basically unchanged.The CFJ rotor airfoil can significantly increase the maximum lift coefficient and the stall angle of attack at high angle of attack.The maximum lift coefficient can be increased by about 67.5%,and the stall angle of attack is significantly delayed by nearly 14.8°.http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2021062?st=article_issueco-flow jetlift enhancement and drag reductionactive flow controlrotor airfoillow-speed wind tunnel test |
| spellingShingle | ZHANG Shunlei YANG Xudong SONG Bifeng WANG Bo LI Zhuoyuan Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept Hangkong gongcheng jinzhan co-flow jet lift enhancement and drag reduction active flow control rotor airfoil low-speed wind tunnel test |
| title | Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept |
| title_full | Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept |
| title_fullStr | Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept |
| title_full_unstemmed | Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept |
| title_short | Experimental Investigation of Lift Enhancement and Drag Reduction of Rotor Airfoil Using Co-flow Jet Concept |
| title_sort | experimental investigation of lift enhancement and drag reduction of rotor airfoil using co flow jet concept |
| topic | co-flow jet lift enhancement and drag reduction active flow control rotor airfoil low-speed wind tunnel test |
| url | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2021062?st=article_issue |
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