椭圆翼型动态失速流场模态分解与重构

曾揚洋; 曾聪; 赵国庆; 李春华; 招启军

doi:10.7638/kqdlxxb-2024.0209

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椭圆翼型动态失速流场模态分解与重构

研究论文 | 更新时间：2026-05-28

- 椭圆翼型动态失速流场模态分解与重构
- Mode decomposition and reconstruction of dynamic stall flow field of an elliptic airfoil
- 空气动力学学报 2025年43卷第7期页码：28-41
- 作者机构：
  
  1. 南京航空航天大学直升机动力学全国重点实验室,南京,210016
  2. 中航工业直升机设计研究所,景德镇,333001
- 作者简介：
  
  曾揚洋，男，博士研究生，研究方向：共轴刚性旋翼气弹耦合. E-mail：nuaa_zyy@nuaa.edu.cn
  招启军*，男，教授，博士生导师，研究方向：直升机旋翼空气动力学、计算流体力学、计算声学和流动主动控制等. E-mail：zhaoqijun@nuaa.edu.cn
- 基金信息：
  
  国家自然科学基金（12032012）
- DOI：10.7638/kqdlxxb-2024.0209
  中图分类号： V211.3
- 纸质出版：2025
- 稿件说明：
移动端阅览
曾揚洋, 曾聪, 赵国庆, 等. 椭圆翼型动态失速流场模态分解与重构[J]. 空气动力学学报, 2025, 43(7): 28−41.

ZENG Yangyang, ZENG Cong, ZHAO Guoqing, et al. Mode decomposition and reconstruction of dynamic stall flow field of an elliptic airfoil[J]. 2025, 43(7): 28-41.
曾揚洋, 曾聪, 赵国庆, 等. 椭圆翼型动态失速流场模态分解与重构[J]. 空气动力学学报, 2025, 43(7): 28−41. DOI： 10.7638/kqdlxxb-2024.0209

ZENG Yangyang, ZENG Cong, ZHAO Guoqing, et al. Mode decomposition and reconstruction of dynamic stall flow field of an elliptic airfoil[J]. 2025, 43(7): 28-41. DOI： 10.7638/kqdlxxb-2024.0209.

摘要

为深入研究椭圆翼型动态失速特性、捕捉流场非定常结构，首先基于非定常雷诺平均纳维-斯托克斯方程，并通过SST

、

θt

进行湍流和转捩建模，建立了一套适用于椭圆翼型流场模拟的数值方法。随后，对相对厚度为16%的椭圆翼型深度动态失速的工况进行了数值模拟，并在时域上对流场非定常特征、气动力系数变化规律进行了深入分析。通过动态模态分解技术对速度和压力进行了特征提取，并以模态能量占比为理论基础，建立了共轭模态的截取方法，开展了流场重构与误差评估。结果表明，椭圆翼型在抬头侧前缘处产生的分离泡是其动态失速涡形成的重要征兆，各阶模态能有效描述动态失速的动力学特征，且与时域上的主要流动特征存在一致性。在各阶模态之中，一阶模态为静态模态，体现出翼型深度失速的流动特征，而流场的非定常结构则来源于共轭模态的贡献。除去一阶模态，采用75%～95%能量占比的共轭模态重构流场能一定程度地反映气动力系数在时域上的变化规律，但无法准确描述精细的非定常细节；采用99%能量占比的共轭模态重构流场，虽然在翼型发生严重流动分离的时刻存在着较大的误差且在捕捉近壁分离泡的流动细节上精度有限，但在重构气动力系数上具有较高的精度和较为有效的模型降维能力，在工程上具有应用价值。

Abstract

In order to investigate the dynamic stall characteristics of elliptic airfoils and capture the main unsteady structures of the flow field

a numerical method was established based on unsteady Reynolds-averaged Navier-Stokes equations with SST

and

θt

turbulence transition models. The method

was applied to simulate deep dynamic stall of an elliptic airfoil with a relative thickness of 16%. The unsteady characteristics of the flow field and the variations of aerodynamic coefficient were thoroughly discussed in the time domain. Dynamic mode decomposition (DMD) was employed to extract the characteristics of velocity and pressure fields

followed by flow field reconstruction and error evaluation using a conjugate-mode truncation method based on the theory of modal energy proportion. The results showed that the separation bubbles generated by the elliptic airfoil at the leading edge during the upstroke process served as a precursor to dynamic stall vortex formation. The modes of each order effectively characterized the dynamics of dynamic stall

consistent with the main flow features in the time domain. While conjugate modes contributed to the unsteady components of the flow field

the first-order DMD mode reflected the uniform flow field with characteristics of deep stall of the airfoil. Excluding the first-order mode

the reconstructed flow field retaining 75%—95% energy of the conjugate modes captured variations of the aerodynamic coefficients in the time domain to a certain extent

but failed to describe fine unsteady details accurately. The reconstructed flow field using 99% energy of the conjugate modes demonstrated a decent accuracy in aerodynamic coefficient prediction and effectiveness in dimensionality reduction despite certain deciations during severe flow separation and limited accuracy in capturing fine flow details of near-wall separation bubbles

showing promising potential for engineering applications.

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Keywords

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