翼梢小翼

翼梢小翼和C型翼梢对基本机翼的颤振特性产生了明显不利影响。

Contrastive analyses indicate that the winglet and C-type wingtip produce remarkable adverse effects on flutter characteristics of transport wing .

最后初步研究了变体翼梢小翼的闭环控制方法。

Finally , the closed-loop control system for the morphing winglet has been presented as well .

CK-1飞机带翼梢小翼的亚音速升阻特性分析

An Analysis of the Lift and Drag Effciency for the CK-1 Aircraft with Winglets at Subsonic Speed

采用Lagrange乘数优化方法，约束升力系数和机翼翼根弯矩，通过修改机翼+翼梢小翼组合体的结构外形，减小机翼的诱导阻力和形状阻力，提高机翼的展向效率和升阻比的大小。

The Lagrange multipliers optimization method is presented for wing + winglet configuration with constraint for lifting coefficient and wing root bending moment . By shaping the wing with winglet , decrease the sum of induced drag and profile drag , increase span efficiency and lift-drag ratio .

本文应用有限基本解法（涡格法）及联合流场概念，计算出CK-1机带翼梢小翼的升力系数及诱导阻力系数。

The lift coefficient and induced drag coeffcient of the CK-1 wing with winglets are calculated in . this paper by the vortex-lattice method and the concept of united flowfield being used .

减阻是飞机设计的主要任务之一，翼梢小翼能有效降低飞机的诱导阻力。

Drag reduction is one of the main goals in aircraft design .

民用飞机翼梢小翼多约束优化设计

The optimal design of civil aircraft winglet with multiple constraint

基于径向基函数的机翼和翼梢小翼外形优化

Shape Parameter Optimization for Wing and Wingtip Based on RBF

翼梢小翼影响一部分名为诱导阻力的阻力。

Winglets affect the part of drag called induced drag .

翼梢小翼的气动特性计算和实验验证

Calculation of aerodynamic characteristics of winglets and experimental verification

采用有限元仿真与风洞试验验证了可变倾角翼梢小翼的变形能力。

The morphing capability is validated by finite element analysis and wind tunnel test .

因此，采用伸缩栅格的变体翼梢小翼具有改善飞机起飞性能的潜力。

Therefore , morphing winglet with retractable grid has the potential of improving aircraft takeoff performance .

到目前为止，世界各国大型运输机加装翼梢小翼已经越来越普遍。

So far , it becomes more and more popular to amount winglets on the large transport aircraft over the world .

传统翼梢小翼主要针对巡航状态设计，无法在起降、爬升阶段提供最佳减阻效果。

Traditional winglets are designed mainly for the cruising stage , while the effects of winglets in the climbing / landing stage are not as significant .

为了提高数值计算效率和准确性，提出了基于多级响应面法的确定翼梢小翼气动外形参数的一种优化方法。

In order to improve the efficiency and accuracy of the numerical calculation for the aerodynamic design of winglets , an optimization method based on multi-level response surfaces is proposed .

翼梢小翼可以有效抑制翼尖涡，减小诱导阻力。

Winglets can be used to inhibit wingtip vortex and to reduce the induced drag effectively , which guarantees the reduction of flight cost and improvement of climbing / landing performance .

与单独优化翼梢小翼外形参数相比，机翼和翼梢小翼一体化设计更有利于提高飞机的气动性能，具有更广泛的工程应用前景。

Compared with the winglet-only shape optimization , the wing-and-winglet integrated design is more conducive to improve the aerodynamic performance of aircraft , and has a wider range of engineering application prospects .

对带翼梢小翼亚音速矩形翼进行了升力计算，并用联合流场法计算了诱导阻力。

A constant roll-angle method is used to divide spanwise lattices and to determine spanwise locations of control points , and the induced drags are calculated by the combined flow field method .

飞机加装翼梢小翼后可以增升减阻、节省燃油，从而增加飞机的航程或有效装载，具有十分重要的经济效益。

After the installation of winglets , the lift of aircraft can be increased , while drag and fuel are reduced , leading to an increase of range and load , which can bring us great economic benefits .