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| 双垂尾对边条翼布局大迎角升力影响机理研究 | |
| 引用本文： | 郑遂,李桂生,蔡广平,昂海松.双垂尾对边条翼布局大迎角升力影响机理研究[J].空气动力学学报,2011,29(2). |
| 作者姓名： | 郑遂 李桂生 蔡广平 昂海松 |
| 作者单位： | 1. 南京航空航天大学航空宇航学院,江苏南京,210016;成都飞机设计研究所,四川成都,610041 2. 成都飞机设计研究所,四川成都,610041 3. 南京航空航天大学航空宇航学院,江苏南京,210016 |
| 摘 要： | 对边条翼双垂尾布局的垂尾导致大迎角升力减小现象的机理进行了研究。采用CFD方法分析一个类似于F-22战斗机的模型,发现在低速大迎角条件下,脱体涡流经垂尾外侧;垂尾下部附近气流方向向后并向外;垂尾外侧存在低压区,而垂尾内侧和垂尾间的机身上表面存在高压区。认为脱体涡在垂尾外侧表面产生吸力,在涡核下方诱导出向外的速度分量,致使垂尾处于侧滑气流中,从而使其表面压力内高外低,除了产生指向外侧的法向力外,也传递内侧高压至机身上表面。外倾垂尾上向外的法向力和机身上表面的高压区,是减小大迎角升力的直接原因。 |
| 关 键 词： | 边条翼布局 双垂尾 前体涡 大迎角 升力 |
A study on the effects of the twin-tails on the lift of a LEX-wing configuration at high AOA |
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| ZHENG Sui,LI Gui-sheng,CAI Guang-ping,ANG Hai-song.A study on the effects of the twin-tails on the lift of a LEX-wing configuration at high AOA[J].Acta Aerodynamica Sinica,2011,29(2). | |
| Authors: | ZHENG Sui LI Gui-sheng CAI Guang-ping ANG Hai-song |
| Institution: | ZHENG Sui1,2,LI Gui-sheng2,CAI Guang-ping2,ANG Hai-song1(1.College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China,2.Chengdu Aircraft Design & Research Institute,Chengdu 610041,China) |
| Abstract: | It was often seen in the wind tunnel tests that a leading edgy extension wing(LEX-wing) configuration suffered a significant reduction of the lift at high AOA when twin-tails was incorporated.To find the reason,a CFD method was used on a model similar to F-22 fighter.It was found that at high AOA the LEX vortices passed through the field outside both vertical tails and induced the airflow below outboard.It was also found that the pressure was lower on the outboard surfaces of the tails and higher on the inb... |
| Keywords: | LEX-wing configuration twin-tails LEX vortex high AOA lift |
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