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首页> 外文会议>International Conference on Computer Aided Optimum Design in Engineering; 2007; Myrtle Beach,SC(US) >Aerodynamic optimization of a biplane configuration using differential evolution
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Aerodynamic optimization of a biplane configuration using differential evolution

机译：使用差分进化对双翼飞机构型进行空气动力学优化

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This paper presents our work on designing a biplane configuration that has a minimum drag to lift ratio. This problem is a mixed optimization problem in that both discrete and continuous variables are used. Fourteen parameters were used to fully describe the biplane configuration and calculate performance. Performance calculations were based on Munk's general biplane theory. Each wing required six parameters; airfoil profile type, span, tip and root chord lengths, angle of attack, and sweep angle. Two parameters were used to define the horizontal stagger and vertical gap between the two planes. The airfoil profile types were stored in an indexed database which allowed us to obtain the section's aerodynamic characteristics. Our analysis showed that differential evolution found the optimum solution quickly. The characteristics of the resultant optimum solution will be discussed in detail, along with our observations of how the process needs to be adjusted for optimum performance.
机译：本文介绍了我们在设计双翼飞机配置中的工作，该配置具有最小的阻力提升比。此问题是混合优化问题，因为同时使用了离散变量和连续变量。使用14个参数来全面描述双翼飞机的配置并计算性能。性能计算基于蒙克的通用双翼飞机理论。每个机翼需要六个参数。翼型轮廓类型，跨度，叶尖和根弦长度，迎角和后掠角。使用两个参数来定义两个平面之间的水平交错和垂直间隙。翼型轮廓类型存储在索引数据库中，这使我们能够获取截面的空气动力学特性。我们的分析表明，差分进化很快找到了最佳解决方案。我们将详细讨论所得最佳解决方案的特性，以及我们对如何调整过程以实现最佳性能的观察。

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