变体翼梢小翼的减阻机理数值模拟  

Numerical simulation on morphing winglets for its drag reduction mechanisms

作　　者：张庆峰[1,2] 熊克[3] 李伟[4] 陈爽[5] 

机构地区：[1]中国民用航空飞行学院飞行技术学院,四川广汉618307 [2]南京航空航天大学民航/飞行学院,南京210016 [3]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 [4]上海工程技术大学航空运输学院,上海201620 [5]中国民用航空飞行学院飞机修理厂,四川广汉618307

出　　处：《航空动力学报》2014年第5期1105-1111,共7页Journal of Aerospace Power

基　　金：基金项目:预先研究

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.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 takeoffphase 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.

关 键 词：减阻 翼梢小翼 气动载荷 气动性能 翼尖涡 

分 类 号：V224.3[航空宇航科学与技术—飞行器设计]