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以NACA0012翼型为基础建立尾缘襟翼模型,采用多学科设计优化框架软件Isight、CFD(计算流体力学)软件Fluent(CFD软件包)以及遗传优化算法,对翼型的气动特性进行优化设计,研究了襟翼不同攻角和摆角对翼型气动性能的影响。基于遗传算法原理建立了优化模型,运用CFD数值模拟方法对流场特性进行分析,以升力系数和升阻比之和为目标函数进行寻优,得到使翼型气动性能最优的参数。结果表明:攻角α=12.183°、襟翼摆动角度为θ=1.100 0°时翼型的气动性能最佳,优化后翼型的升阻比增加了16%,升力系数增加了10.1%,同时也证明多岛遗传算法在翼型气动性能优化中的可行性。
Based on the NACA0012 airfoil, the tail flap model is established. The aerodynamic characteristics of the airfoil are optimized by Isight CFD (CFD software package) and genetic optimization algorithm. The influence of different angles of attack and swing angle on the aerodynamic performance of airfoil is studied. Based on the principle of genetic algorithm, an optimization model was established. The CFD numerical simulation method was used to analyze the characteristics of the flow field. The sum of the lift coefficient and the drag-and-drag ratio was used as the objective function to obtain the optimal aerodynamic parameters of the airfoil. The results show that the airfoil has the best aerodynamic performance when the angle of attack is α = 12.183 ° and the flap swing angle is θ = 1.100 0 °. The optimized lift ratio of airfoil increases by 16% and the lift coefficient increases by 10.1% It also proves the feasibility of multi-island genetic algorithm in aerodynamic performance optimization of airfoils.