| 尖顶弯折三角翼气动特性研究 |
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| 引用本文： | 展京霞, 徐燕, 王晋军. 尖顶弯折三角翼气动特性研究[J]. 力学与实践, 2002, 24(3): . doi: 10.6052/1000-0992-2001-090 |
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| 作者姓名： | 展京霞 徐燕 王晋军 |
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| 作者单位： | 北京航空航天大学飞行器设计与应用力学系 100084; 北京航空航天大学飞行器设计与应用力学系 100084; 北京航空航天大学飞行器设计与应用力学系 100084 |
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| 基金项目： | 国防科技预先研究基金资助． |
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| 摘 要： | 对75°后掠三角翼在40%根弦处弯折引起的升阻特性及俯仰特性的变化进行了低速风洞实验研究，初步分析了尖顶弯折对三角翼气动特性的影响趋势. 得出尖顶弯折在低速大攻角下，可以使升力系数Cy增大、升阻比提高，并推迟失速攻角amax，从而说明顶部弯折对三角翼气动特性的改善作用是显著的.
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| 关 键 词： | 三角翼 尖顶弯折角 风洞实验 升力系数 升阻比 |
| 收稿时间： | 2001-03-09 |
| 修稿时间： | 2001-03-09 |
EXPERIMENTAL INVESTIGATION ON THE AERODYNAMIC CHARACTERISTICS OF DELTA-WINGS WITH APEX FLAP |
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| ZHAN Jingxia XU Yan WANG JinjunThe. EXPERIMENTAL INVESTIGATION ON THE AERODYNAMIC CHARACTERISTICS OF DELTA-WINGS WITH APEX FLAP[J]. Mechanics and Engineering, 2002, 24(3): 0-0. DOI: 10.6052/1000-0992-2001-090 |
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| Authors: | ZHAN Jingxia XU Yan WANG JinjunThe |
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| Affiliation: | ZHAN Jingxia XU Yan WANG JinjunThe Department of Flight Vehicle Design and AppliedMechanics,Beijing 100083,China |
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| Abstract: | The variations of the lift coefficient,drag coefficient and pitch moment due to the apexflap located at 40 percent of the root chord of adelta-wing are investigated in the low-speed windtunnel. The experiment indicates the influence ofthe apex flap. It is shown that the apex flap canenhance the lift coefficient, lift-drag ratio and stallangle of attack. Thus, it can be concluded thatthe apex flap may greatly improve the aerodynamiccharacteristics of a delta-wing. |
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| Keywords: | delta-wing apex flap wind tunnel ex-periment lift coefficient lift-drag ratio |
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