基于伴随算法的翼型优化设计  

Airfoil Optimal Design Based on Adjoint Algorithm

作　　者：邓建军 段治强 邓建华 DENG Jianjun;DUAN Zhiqiang;DENG Jianhua(Chengdu Aeronautic Polytechnic,Chengdu,Sichuan Province,610100 China)

机构地区：[1]成都航空职业技术学院,四川成都610100

出　　处：《科技创新导报》2022年第28期52-55,93,共5页Science and Technology Innovation Herald

基　　金：省域节能减碳产业质量提升与应用示范,四川省科技计划项目,四川省科学技术厅(项目编号:2020GFW002)。

摘　　要：本文采用伴随算法和CFD方法对NACA0012翼型进行了以提高升阻比为目的的优化设计,并通过多个计算工况来验证伴随算法的适应性。计算结果表明,不同攻角下,伴随算法均可有效提升翼型的升阻比,但其优化效率会随着攻角的增加而降低,相比于原始翼型,升阻比最大增加了32.55%,证明了本文方法的可行性和有效性。通过翼型表面压力系数分布可知,伴随算法主要通过增大翼型下表面压力,减小翼型上表面压力来提升翼型升力,算法简单易行,计算过程稳定可靠。In this paper,the adjoint algorithm and CFD method are used to optimize the design of NACA0012 airfoil for the purpose of improving the lift-drag ratio,and the adaptability of the adjoint algorithm is verified by several calculation conditions.The calculation results show that the adjoint algorithm can effectively improve the lift-drag ratio of the airfoil at different angles of attack,but its optimization efficiency decreases with the increase of the angle of attack.Compared with the original airfoil,the lift-drag ratio increases by 32.55%,which proves the feasibility and effectiveness of the proposed method.According to the distribution of pressure coefficients on the airfoil surface,the adjoint algorithm can improve the airfoil lift mainly by increasing the pressure on the lower surface of the airfoil and reducing the pressure on the upper surface of the airfoil.The algorithm is simple and feasible,and the calculation process is stable and reliable.

关 键 词：伴随算法 升阻比优化 压强系数 计算流体力学 

分 类 号：V224[航空宇航科学与技术—飞行器设计] TP391.9[自动化与计算机技术—计算机应用技术]