风力机翼型在大攻角流场下的动力模态分解分析

发布时间：2019-01-05 13:45

【摘要】：采用计算流体动力学(CFD)方法,在恒定大攻角工况下,对风力机翼型的非定常流场进行数值模拟,并采用动力模态分解(DMD)方法对其模态进行辨识,以得到非定常流场的频率和相应的主要模态.结果表明:DMD方法可用于分析非定常流场的变化过程;DMD的各阶模态描述了非定常流场的主要流动特征,流场中非定常流动主要集中在近尾迹区域;采用包含主要流动信息的前4阶模态重构的流场能够反映不同时刻的时域流场;第2阶DMD模态重构的流场可以直观地描述尾迹区域内2个方向相反的涡依次脱落并向下游传播的非定常流动特征.
[Abstract]:The unsteady flow field of the wind wing is numerically simulated under the condition of constant angle of attack by using the computational fluid dynamics (CFD) method, and the modal identification of the unsteady flow field of the wind wing is carried out by using the dynamic mode decomposition (DMD) method. The frequency of the unsteady flow field and the corresponding main modes are obtained. The results show that the DMD method can be used to analyze the variation of unsteady flow field, and the main flow characteristics of unsteady flow field are described by DMD modes, and the unsteady flow in the flow field is mainly concentrated in the near wake region. The flow field with the first four modes including the main flow information can reflect the time domain flow field at different times. The flow field of the second order DMD modal reconstruction can directly describe the unsteady flow characteristics of two opposite vortices in the wake region which shedding in turn and propagating downstream.
【作者单位】：上海交通大学机械与动力工程学院;上海飞机制造有限公司理化计量中心;
【基金】：国家自然科学基金项目(51506123)资助
【分类号】：O35

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