论文部分内容阅读
应用基于代理模型的优化方法对35%相对厚度、后缘安装隔板的平底后缘风力机翼型进行优化设计。基于雷诺平均Navier-Stokes方程,采用耦合γ-_(eθ)转捩模型的SST k-ω湍流模型,对平底后缘翼型绕流进行数值模拟得到翼型的气动性能。以翼型在大迎角下的升力系数和截面惯性矩为目标,阻力系数和力矩系数等为约束,对平底后缘翼型进行优化设计;结果表明,优化后翼型在满足约束条件的同时,迎角17°时,升力系数提高8.53%,最大升力系数较基准翼型提高3.13%,截面惯性矩较基准翼型提高7.84%。
The optimization model based on the agent model was used to optimize the airfoil of the flat-bottom trailing edge of the 35% relative thickness and rear mounting partition. Based on the Reynolds-averaged Navier-Stokes equation, the aerodynamic performance of the airfoil is obtained by numerical simulation of the SST k-ω turbulence model coupled with γ- eθ transition model. Taking the lift coefficient and moment of inertia of airfoil at high angle of attack as target, the drag coefficient and torque coefficient as constraints, the optimal design of flat-bottomed trailing edge airfoil is carried out. The results show that the optimized airfoil can satisfy the constraint condition And 17 ° angle of attack, the lift coefficient increased by 8.53%, the maximum lift coefficient increased by 3.13% compared with the reference airfoil, and the moment of inertia of the cross section increased by 7.84% compared with the reference airfoil.