| 变体翼梢小翼的减阻机理数值模拟 |
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| 引用本文： | 张庆峰,熊克,李伟,陈爽.变体翼梢小翼的减阻机理数值模拟[J].航空动力学报,2014,29(5):1105-1111. |
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| 作者姓名： | 张庆峰 熊克 李伟 陈爽 |
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| 作者单位： | 中国民用航空飞行学院 飞行技术学院, 四川 广汉 618307;南京航空航天大学 民航/飞行学院, 南京 210016;南京航空航天大学 航空宇航学院 机械结构力学及控制国家重点实验室, 南京 210016;上海工程技术大学 航空运输学院, 上海 201620;中国民用航空飞行学院 飞机修理厂, 四川 广汉 618307 |
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| 摘 要： | 总结了对翼梢小翼减阻效果影响最大的几何参数,在此基础上采用数值模拟方法研究了这些几何参数的最佳变化范围,为变体翼梢小翼设计提供理论依据.并从气动性能、气动载荷分布和翼尖涡的角度探讨了变体翼梢小翼相对传统翼梢小翼的优缺点.结果表明:在飞机的起飞阶段,变体翼梢小翼的减阻效率比传统翼梢小翼高2.2%,同时将翼尖涡强度降低了15%,有利于提高飞机的燃油效率和机场空域安全;但也会增大机翼的翼根弯矩,因此必须权衡变体翼梢小翼带来的气动收益与结构强度不利因素.
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| 关 键 词： | 减阻 翼梢小翼 气动载荷 气动性能 翼尖涡 |
| 收稿时间： | 2013/6/16 0:00:00 |
Numerical simulation on morphing winglets for its drag reduction mechanisms |
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| ZHANG Qing-feng,XIONG Ke,LI Wei and CHEN Shuang.Numerical simulation on morphing winglets for its drag reduction mechanisms[J].Journal of Aerospace Power,2014,29(5):1105-1111. |
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| Authors: | ZHANG Qing-feng XIONG Ke LI Wei and CHEN Shuang |
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| Institution: | Flight Technology College, Civil Aviation Flight University of China, Guanghan Sichuan 618307, China;College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;State Key Laboratory of Mechanics and Control of Mechanical Structures, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;School of Air Transportion, Shanghai University of Engineering Science, Shanghai 201620, China;Aircraft Repair and Overhaul Plant, Civil Aviation Flight University of China, Guanghan Sichuan 618307, China |
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| Abstract: | The most critical geometric parameters of winglets in drag reduction efficiency were summarized. Then the numerical simulation method was utilized to reveal the optimal range of these parameters, which is the theoretical basis of morphing winglet design. The advantages and disadvantages of morphing winglets in aerodynamic performance, aerodynamic load distribution and wingtip vortices were discussed compared with traditional winglets. The results show that morphing winglets can increase the drag reduction efficiency by 2.2% compared with traditional winglets and weaken the wingtip vortices by 15% in the takeoff phase of flight. It is beneficial to enhance the fuel efficiency of aircraft and the airport spatial security. However, morphing winglets increase the bending moment at the wing root. For this reason, aircraft designers have to strik a balance between the aerodynamic benefits and the structural disadvantages in morphing winglet designs. |
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| Keywords: | drag reduction winglet aerodynamic load aerodynamic performance wingtip vortices |
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