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针对低速通用飞机升阻特性的低成本精细化设计,通过合理地简化模型,建立了一种将翼型升阻比曲线斜率作为附加设计约束的机翼工程优化设计方法。基于该优化设计方法,利用低成本快速设计分析工具开展了优化设计,并对设计方法及结果进行了风洞试验验证。试验结果表明,所提方法能够有效提高机翼最大升阻比,同时使最大升阻比对应的升力系数逼近巡航工况,进一步挖掘了低速通用飞机的经济性潜力。
In order to reduce the cost and refinement design of low-speed general-purpose aircraft’s lift-drag characteristic, an optimal design method of wing engineering is proposed by simplifying the model reasonably with an additional design constraint. Based on the optimized design method, the optimization design was carried out by using low-cost rapid design and analysis tools, and the wind tunnel test was conducted to verify the design method and results. The experimental results show that the proposed method can effectively improve the maximum lift-drag ratio of the wing and at the same time, make the lift coefficient corresponding to the maximum lift-drag ratio approach the cruising condition, further exploring the economic potential of the low-speed general aircraft.