| 前缘缝翼构型平尾直升机气动特性分析 |
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| 引用本文： | 王鑫磊,李生伟,林长亮.前缘缝翼构型平尾直升机气动特性分析[J].南京航空航天大学学报,2020,52(2):288-293. |
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| 作者姓名： | 王鑫磊 李生伟 林长亮 |
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| 作者单位： | 哈尔滨哈飞航空工业有限责任公司飞机设计所,哈尔滨,150066;哈尔滨哈飞航空工业有限责任公司飞机设计所,哈尔滨,150066;哈尔滨哈飞航空工业有限责任公司飞机设计所,哈尔滨,150066 |
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| 摘 要： | 使用数值模拟方法研究了前缘缝翼翼型气动特性,并将该前缘缝翼翼型应用于直升机平尾,分析了该直升机全机气动特性,最后通过风洞试验对数值模拟结果进行验证。结果表明,前缘缝翼构型平尾能有效改善直升机的纵向静稳定性。
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| 关 键 词： | 直升机 前缘缝翼 平尾 风洞试验 纵向静稳定性 |
| 收稿时间： | 2019/3/6 0:00:00 |
| 修稿时间： | 2019/12/26 0:00:00 |
Aerodynamic Characteristics of Helicopter with Leading-Edge Slatted Horizontal Tail |
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| WANG Xinlei,LI Shengwei,LIN Changliang.Aerodynamic Characteristics of Helicopter with Leading-Edge Slatted Horizontal Tail[J].Journal of Nanjing University of Aeronautics & Astronautics,2020,52(2):288-293. |
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| Authors: | WANG Xinlei LI Shengwei LIN Changliang |
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| Institution: | Harbin Hafei Aviation Industry Co., Ltd., Aircraft Design Institute, Harbin, 150066,China |
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| Abstract: | Aerodynamic characteristics of the slatted airfoil are investigated by using numerical simulation techniques. The slatted airfoil to a helicopter s horizontal tail is applied. The aerodynamic characteristics of the whole helicopter are calculated and analyzed. Then wind tunnel tests are conducted to validate the simulation results. The results show that the horizontal tail with a leading-edge slat can effectively improve the longitudinal static stability of the helicopter. |
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| Keywords: | helicopter slatted airfoil horizontal tail wind tunnel test longitudinal static stability |
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