IDDES simulations of flow separation around the iced airfoil and its modal analysis

DU Menghua; TIAN Linlin; ZHU Chunling

doi:10.7638/kqdlxxb-2022.0140

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IDDES simulations of flow separation around the iced airfoil and its modal analysis

更新时间：2026-05-28

- IDDES simulations of flow separation around the iced airfoil and its modal analysis
- Vol. 41, Issue 11, Pages: 46-55(2023)
- 作者机构：
  
  南京航空航天大学航空学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0140
  CLC： V211.3
- Published：2023
- 稿件说明：
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杜孟华, 田琳琳, 朱春玲. 带冰翼型失速分离流动数值模拟和模态分析[J]. 空气动力学学报, 2023, 41(11): 46−55.

DU Menghua, TIAN Linlin, ZHU Chunling. IDDES simulations of flow separation around the iced airfoil and its modal analysis[J]. 2023, 41(11): 46-55.
杜孟华, 田琳琳, 朱春玲. 带冰翼型失速分离流动数值模拟和模态分析[J]. 空气动力学学报, 2023, 41(11): 46−55. DOI： 10.7638/kqdlxxb-2022.0140

DU Menghua, TIAN Linlin, ZHU Chunling. IDDES simulations of flow separation around the iced airfoil and its modal analysis[J]. 2023, 41(11): 46-55. DOI： 10.7638/kqdlxxb-2022.0140.

摘要

为了对防除冰问题进行精细化模拟和对带冰机翼进行全局稳定性分析，采用改进延迟脱体涡模拟（improve delayed detached-eddy simulation

IDDES）方法，对GLC305翼型带944号冰形表面复杂流动进行了非定常模拟。基于此，分别采用本征正交分解方法（proper orthogonal decomposition

POD）和动态模态分解方法（dynamic mode decomposition

DMD）对模拟结果进行模态分析，以提取影响流动分离的主要模态，最后对流场进行重构。结果表明，IDDES方法准确预测了翼型升力系数和冰角下游的压力平台等特征，清晰地捕捉了冰角后剪切层失稳脱落形成的涡结构及在向下游流动中涡结构合并、破碎的发展过程。基于IDDES获得的非定常数据，POD方法识别出角冰诱导剪切层中的两种典型脉动频率，且在前几阶主要模态中均存在，意味着这两种脉动模式对流动的主导作用。另外，DMD方法得到的每个模态对应单一的频率和放大率，部分模态处于发散状态，这是导致流动不稳定发生的主要机制。研究还发现POD和DMD主要模态的能量序列均从翼型中部开始，这与剪切层失稳位置密切相关。

Abstract

Ice accretion on a wing can seriously affect the flight safety. Analysis on the unsteady flow characteristic of the iced wing

especially of the horn ice near the stall point

is a vexing challenge which receive significant research interest in recent years. In this study

unsteady and complex flow separation around a GLC305 airfoil with 944 horn ice is numerically investigated at first. Besides

the proper orthogonal decomposition (POD) and the dynamic mode decomposition (DMD) are introduced to extract modal features from the turbulent wake behind the three-dimensional wing with ice shape. The results revealed that the IDDES method accurately predicts the lift coefficient and pressure platform behind the horn ice

and clearly captures the vortex structures and its evolution process. The first two modes decomposed by the POD method occupy the main energy

and the frequency corresponding to the time coefficients of the first four modes is consistent with the shear layer oscillation frequency in the experiment. Besides

the dominant frequencies and the corresponding magnifications are extracted with the DMD method. It is found that several highly unstable modes lead to flow separation

because these modes correspond to flow structures that are uncontrolled growth with time. With both the POD and DMD methods

it can be noted that the energy sequences of their main modes occur start from the middle position of the airfoil

which is related to the position where the shear layer loses its stability.

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Keywords

references

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