翼梢小翼影响一部分名为诱导阻力的阻力。
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.
成功的实例设计结果表明，本文方法对民用飞机机翼-翼梢小翼的设计具有应用价值。
The results of practical design showed that this method can be used in the design of winglet.
如此卓著的效率应当归功于低阻机翼、前缘缝翼和双开缝襟翼，以及高马赫混合式翼梢小翼。
This efficiency is due largely to the innovative design of the low-drag wing. This design includes leading-edge slats, double-slotted Fowler flaps, and high-Mach blended winglets.
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.
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.
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