| 融合式翼梢小翼减阻效应研究 |
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| 引用本文： | 马玉敏,魏剑龙.融合式翼梢小翼减阻效应研究[J].航空工程进展,2018,9(2):245-251. |
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| 作者姓名： | 马玉敏 魏剑龙 |
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| 作者单位： | 第一飞机设计研究院总体气动设计研究所 |
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| 摘 要： | 有效减小诱导阻力对于飞机降低油耗、提高航程具有重要意义。针对某飞机翼身组合体构型,采用CFD数值模拟方法分析融合式翼梢小翼对飞机气动力特性的影响,尤其是其减阻效应;并给出翼梢小翼附近的空间流场。结果表明:带翼梢小翼后翼尖涡强度减弱,飞机阻力系数明显下降;固定升力系数0.5时,弯矩增加3.2%,阻力系数减小4.2%。
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| 关 键 词： | 翼梢小翼 气动特性 诱导阻力 减阻 弯矩系数 数值模拟 |
| 收稿时间： | 2017/11/3 0:00:00 |
| 修稿时间： | 2017/12/8 0:00:00 |
Drag Reduction Research on Fusion Winglet |
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| Ma Yumin and Wei Jianlong.Drag Reduction Research on Fusion Winglet[J].Advances in Aeronautical Science and Engineering,2018,9(2):245-251. |
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| Authors: | Ma Yumin and Wei Jianlong |
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| Abstract: | Effectively decreasing induced drag can be significant for the aircraft to reduce the fuel consumption and increase the flight range. Numerical simulation with CFD methods were carried out to obtain the aerodynamic characteristics, especially the drag reduction effect of the fuselage and wing configuration with the fusion winglet. The results showed that tip vortex was decreased and drag coefficient was obviously reduced. The bending moment coefficient can be increased by 3.2% and drag coefficient can be decreased by 4.2% when specifying the lift coefficient to be 0.5. |
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| Keywords: | winglet aerodynamic performance induced drag drag reduction bending moment coefficient numerical simulation |
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