Airfoil robust design with uncertainty parameters
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摘要: 讨论了一种在来流速度不确定的情况下对翼型进行鲁棒性设计的方法.介绍了单点及多点设计方法后,阐述了鲁棒性设计方法在翼型气动性能优化中的应用,并对三者进行了比较.引入了代理模型以减少计算量, 并通过遗传算法对翼型进行鲁棒性设计.借助区间分析方法讨论了翼型设计变量的扰动对气动特性上下界值的影响.应用该方法,在提高了翼型的气动性能的同时,降低了该性能对于来流速度的敏感度.Abstract: A robust design optimization of 2D airfoil with uncertainty of inlet Mach number was presented. Based on NACA0012, a series of geometry as well as boundary parameters were introduced. Three optimization methods, including single-point method, multi-point method as well as robust method,were discussed. Airfoil sample points were obtained using uniform design theory for the response surface training of Kriging model. Consequently the corresponding parameters of the airfoil were identified for optimal robust design with genetic algorithm. The influence of geometry parameters perturbation on the aerodynamic performance was discussed by applying interval analysis method. Compared with the traditional genetic algorithm, the optimization process presented has advantage in terms of time consumption.
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Key words:
- airfoil optimization /
- robust design /
- genetic algorithm /
- interval analysis /
- Kriging model
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