基于DMD方法的结冰对翼型绕流流场低阶模态的影响研究  

Study on the Effects of Icing on Low Order Modes of Flow Field Around Airfoils Based on DMD Method

作　　者：吴雪飞 刘勇[1] 邹宇 胡佳伟 WU Xuefei;LIU Yong;ZOU Yu;HU Jiawei(School of Aeronautics and Astronautics,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]南昌航空大学航空宇航学院,江西南昌330063

出　　处：《郑州航空工业管理学院学报》2025年第1期26-33,共8页Journal of Zhengzhou University of Aeronautics

基　　金：航空科学基金(GA202406079)。

摘　　要：基于大涡模拟(Large Eddy Simulation,LES)方法,对NACA0012翼型在结冰和未结冰两种工况下进行了数值模拟,同时基于动力学模态分解(Dynamic modal decomposition,DMD)方法分析了结冰对翼型非定常流动低阶模态的影响。结果表明,7.5°迎角时,结冰对翼型升力系数幅值的影响较大,随着迎角的增大,结冰对升力系数幅值的影响开始减弱;尤其是在13.5°迎角时,结冰与迎角产生了耦合作用,加强了对升力系数幅值的影响。通过DMD分析发现,在低阶模态下,干净翼型大尺度流动结构在7.5°迎角下具有周期性演变的特性,结冰翼型的大尺度流动结构在13.5°迎角时出现了上述特征;此外还发现,随着迎角增加,干净翼型大尺度流动结构波长变长,而结冰翼型其波长变短,但两种翼型大尺度流动结构所对应的频率都明显降低。Based on the Large Eddy Simulation(LES)method,the NACA0012 airfoil is numerically simulated under two conditions:icing and non-icing.At the same time,the Dynamic Modal Decomposition(DMD)method is used to analyze the effect of icing on the low order modes of unsteady flow of the airfoil.The results show that when the Angle of Attack(AoA)is 7.5°,icing has a greater effect on the amplitude of the lift coefficient of the airfoil.However,with the increase of the AoA,the impact of icing on the amplitude of the lift coefficient begins to diminishes.At an AoA of 13.5°,a coupling effect between icing and the AoA is observed,further strengthening the influence on the amplitude of the lift coefficient.Through DMD analysis,it is found that in the low-order mode,the large-scale flow structure of the clean airfoil exhibits periodic evolution at an AoA of 7.5°,while for the iced airfoil,this characteristic occurs at an AoA of 13.5°.Furthermore,with the increase of the AoA,the wavelength of the large-scale flow structure of the clean airfoil becomes longer,whereas that of the iced airfoil becomes shorter.However,the frequencies corresponding to the large-scale flow structures of both airfoils decrease significantly.

关 键 词：结冰 DMD 流动分离 模态分析 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]