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中文摘要：
减小诱导阻力对大型飞机以及高空长航时无人机具有重要意义。基于升力线理论建立机翼的气动弹性模型，通过优化偏转沿展向分布的前后缘控制面减小诱导阻力。展弦比为8，梢根比为0．8的刚性和弹性机翼优化前后的诱导阻力等结果表明采用偏转控制面减阻的方法可行。具有相同气动面积，但梢根比不同的刚性机翼升力与诱导阻力之比表明，梢根比为0．4左右时其值最大。针对刚度沿展向均匀分布的弹性机翼分析表明，当梢根比为0．2左右时，其升力与诱导阻力之比最大，并且控制面的优化偏转使其翼尖挠度有所降低。相关结论对工程实际中采用有限个控制面减阻具有参考价值。
英文摘要：
The induced drag reduction is an important problem for the commercial transport aircrafts and the high altitude long endurance unmanned aerial vehicles. An aeroelastic model is established based on the lifting-line theory. The induced drag is reduced by deflecting full-span leading- and trailing-edge control surfaces. The aspect ratio of the rigid wing and the elastic wing are 8. When their taper ratio（TR） is 0.8, the results including induced drag distributions etc. show that the above method is efficient. For the rigid wings which have the same area and different taper ratios, the ratio of the lift to the induced drag is best when their TR is about 0.4. For elastic wings whose stiffness distributes uniformly, the ratio of the lift to the induced drag is best when their TR is about 0.2. The deflection of the control surfaces reduces the displacement of the elastic wing tip. The results give out the reference to the drag reduction using a finite number of control sufaces in engineering application.
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