低雷诺数翼型多目标优化设计研究
Multi-objective Optimization Design of Airfoil at Low Reynolds Number
刘宇琪 1夏天宇 1董昊 2程克明1
作者信息
- 1. 南京航空航天大学航空学院,南京 210016;南京航空航天大学非定常空气动力学与流动控制工信部重点实验室,南京 210016
- 2. 南京航空航天大学航空学院,南京 210016;南京航空航天大学非定常空气动力学与流动控制工信部重点实验室,南京 210016;南京航空航天大学航空航天结构力学及控制全国重点实验室,南京 210016
- 折叠
摘要
为消除低雷诺数下对称翼型小迎角范围内的气动力非线性现象,基于高斯过程回归模型及NSGA-Ⅱ多目标遗传算法并耦合RANS的数值方法建立了低雷诺数翼型优化设计程序,以多个状态下小迎角范围内的平均巡航因子为目标函数开展翼型优化设计.结果表明:优化翼型具有明显的几何凸起,有效改变了分离泡的位置和类型,进而显著改善翼型气动特性,Re=4×104 时小迎角范围内的升力系数非线性现象基本消失.进一步分析发现优化翼型的凸起增强了壁面的对流影响和来流抵抗逆压梯度的能力,进而改善了翼型的气动特性.
Abstract
In order to eliminate the nonlinear aerodynamic behaviour of a symmetric airfoil within the low angles of attack at low Reynolds number,this paper establishes a low Reynolds number airfoil optimization design procedure based on Gaussian process regression model and NSGA-Ⅱ multi-objective genetic algorithm coupled with RANS numerical method.Then this paper carries out the airfoil optimization design with the average cruise factor in the range of small angle of attack of multiple states as the objective function.The results show that the optimized airfoil exhibits pronounced geometric bump and effectively alters the position and type of the laminar separation bubble.The aerodynamic characteristics of the airfoil are significantly improved,and the nonlinear phenomenon of the lift coefficient within the small angle of attack range at Re=4×104 basically disappears.Further analysis reveals that the bump of the optimized airfoil enhances the convective influence of the wall,which enhances the resistance of the incoming flow to the upward pressure gradient,thus improving the airfoil aerodynamic characteristics.
关键词
低雷诺数/气动力非线性现象/加点准则/翼型多目标优化/层流分离泡Key words
low Reynolds number/aerodynamic nonlinear phenomena/infill criterion/multi-objective optimization of airfoil/laminar separation bubble引用本文复制引用
出版年
2024
国家科技期刊平台
NSTL
万方数据