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基于势流模型与等几何配点法的机翼翼型优化

Airfoil Optimization with Isogeometric Collocation Based on Potential Flow Model

  • 摘要: 基于空气动力性能数值计算的机翼翼型优化设计可以降低成本, 缩短设计周期, 已逐渐成为目前翼型设计的主要发展方向. 本文提出一种基于势流模型与等几何配点法的机翼翼型优化方法. 利用等几何配点法对不可压缩理想来流下的势流模型求解速度势. 结合叶素理论计算翼型的空气动力特性指标, 即升阻比. 构造包含最大升阻比和最小拟合项的目标函数, 同时保证了翼型的气动性能和外形的光顺性, 运用多种最优化方法求解得到优化后翼型. 实验中, 通过渐进迭代逼近法对三类翼型数据点拟合得到初始翼型的NURBS表示, 优化结果表明该算法不仅保持翼型的自身特点和光顺性, 而且对升阻比性能指标有显著的提升.

     

    Abstract: The airfoil optimization design based on numerical calculation of aerodynamic performance can reduce the cost and shorten the design cycle, which has gradually become the mainstream of airfoil design. This paper presents an optimization method of airfoil based on potential flow model with isogeometric collocation method. Firstly, the velocity potential of the potential flow model under an ideal incompressible flow is solved by using the isogeometric collocation method. Secondly, the aerodynamic characteristic index of airfoil, e.g. lift-to-drag ratio, is calculated based on the Blade Element Theory. Finally, an objective function containing the maximum lift-to-drag ratio and the minimum fitting error is constructed to ensure the aerodynamic performance and smoothness of the airfoil. The optimized airfoil is obtained by utilizing a variety of optimization methods. In the experiment, the NURBS representation of the initial airfoil was acquired by fitting the data points of three types of airfoil by the Progressive Iterative Approximation method. The optimization results show that the algorithm not only keeps the airfoil's own characteristics and smoothness, but also improves the index of lift-to-drag ratio significantly.

     

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