上海交通大学学报

上海交通大学学报 >

2021 , Vol. 55 >Issue 11: 1333 - 1342

DOI: https://doi.org/10.16183/j.cnki.jsjtu.2020.427

近失速形态下冰脊分离非定常流的IDDES和模态分析

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  • a.航空航天学院,上海交通大学,上海 200240
    b.船舶海洋与建筑工程学院,上海交通大学,上海 200240
    c.高性能计算中心,上海交通大学,上海 200240
谭 雪(1996-),女,四川省德阳市人,硕士生,主要从事飞机结冰研究.

收稿日期: 2020-12-21

  网络出版日期: 2021-09-22

基金资助

结冰与防除冰重点实验室开放基金(IADL20190203);上海交通大学新进青年教师启动计划资助项目(20X100040034)

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Unsteadiness and Modal Analysis of Ridge Ice-Induced Separation in Post-Stall Conditions via IDDES

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  • a. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China
    b. School of Naval Architecture, Ocean and Civil Engineering, Shanghai Jiao Tong University, Shanghai 200240, China
    c. Center for High Performance Computing, Shanghai Jiao Tong University, Shanghai 200240, China

Received date: 2020-12-21

  Online published: 2021-09-22

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摘要

采用改进延迟脱体涡模拟 (IDDES) 方法,对近失速条件下溢流冰脊诱导的剪切层振荡现象进行高分辨率模拟,描述高雷诺数下冰脊分离流大尺度分离的流场演化特征.研究表明,近失速形态下,冰脊和下翼面尾缘同时诱导出剪切流动,冰脊诱导的剪切层并未再附到壁面,与下翼面上洗流动相互干扰,形成大尺度低能态结构.结合频谱分析进一步发现,剪切层内的压力脉动存在两种典型的脉动频率,与Kelvin-Helmholtz不稳定性相关,具体表现为涡配对和涡脱落.基于正交分解得到的压力脉动主导模态为剪切层之间的大尺度相干结构.主导模态的时间系数与升力系数的功率密度谱峰值保持一致,这说明尾缘区大尺度相干结构与升力波动具有相关性.

关键词： 溢流冰脊; 剪切层振荡; 数值模拟; 频谱分析; 模态分析

本文引用格式

谭雪, 张辰, 徐文浩, 王福新, 文敏华 . 近失速形态下冰脊分离非定常流的IDDES和模态分析[J]. 上海交通大学学报, 2021 , 55(11) : 1333 -1342 . DOI: 10.16183/j.cnki.jsjtu.2020.427

Abstract

High-resolution simulation of shear layer oscillation induced by ridge ice in post-stall condition is conducted via the improved delayed detached-eddy simulation (IDDES) method. The flow-field evolution characteristics of large scale separation in high Reynolds number condition are described. It is shown that the ridge ice and trailing edge of the lower surface induce the development of shear flow at the same time. The wall is not reattached by the shear layer induced by ridge ice, and the “up-wash” flow from the lower surface is interacted with the shear layer, which lead to the formation of large-scale coherent structures. Combined with the spectral analysis, the pressure pulsation located in the shear layer is characterized by two typical frequencies, which are associated with Kelvin-Helmholtz instability and appear as the vortex pairing and shedding. Based on the proper orthogonal decomposition, the dominant mode of pressure pulsation between shear layers is extracted as large-scale coherent structures. The same peak value is shown in power density spectrum of dominant mode temporal coefficient and lift coefficient, which indicates that the large-scale coherent structure is connected with lift fluctuation.

Key words： ridge ice; shear layer oscillation; numerical simulation; spectrum analysis; modal analysis

参考文献

[1] 顾洪宇, 桑为民, 庞润, 等. 机翼热气防冰及冰脊形成数值模拟[J]. 气体物理, 2019, 4(4):41-49.
[1] GU Hongyu, SANG Weimin, PANG Run, et al. Numerical simulation of wing hot air anti-icing and ice ridge formation[J]. Physics of Gases, 2019, 4(4):41-49.
[2] ZHANG C, LIU H. Effect of drop size on the impact thermodynamics for supercooled large droplet in aircraft icing[J]. Physics of Fluids, 2016, 28(6):062107.
[3] POURYOUSSEFI S G, MIRZAEI M, NAZEMI M M, et al. Experimental study of ice accretion effects on aerodynamic performance of an NACA 23012 airfoil[J]. Chinese Journal of Aeronautics, 2016, 29(3):585-595.
[4] ZHANG Y, HABASHI W G, KHURRAM R A. Zonal detached-eddy simulation of turbulent unsteady flow over iced airfoils[J]. Journal of Aircraft, 2015, 53(1):168-181.
[5] 李焱鑫, 顾新. 民机SLD结冰研究和适航验证的发展与挑战[J]. 中国民航大学学报, 2020, 38(4):48-53.
[5] LI Yanxin, GU Xin. Development and challenges of supercooled large drop icing research for civil airplane airworthiness certification[J]. Journal of Civil Aviation University of China, 2020, 38(4):48-53.
[6] Federal Aviation Administration. Federal Aviation Administration on airplane and engine certification requirements in supercooled large drop, mixed phase, and ice crystal icing condition [EB/OL]. (2014-04-11)[2019-12-13]. http://www.federalregister.gov/documents/2014/11/04/2014-25789/airplane-and-engine-certification-requirements-in-supercooled-large drop-mixed-phase-and-ice-crystal-icing-condition.
[7] BROEREN A, BRAGG M. Effect of airfoil geometry on performance with simulated intercycle ice accretions[C]// 41st Aerospace Sciences Meeting and Exhibit. Reston, Virginia, USA: AIAA, 2003: 1-16.
[8] LEE S, BRAGG M B. Investigation of factors affecting iced-airfoil aerodynamics[J]. Journal of Aircraft, 2003, 40(3):499-508.
[9] 李冬, 张辰, 王福新, 等. 结冰对带舵面翼型流场的影响及其气动参数分析[J]. 上海交通大学学报, 2017, 51(3):367-373.
[9] LI Dong, ZHANG Chen, WANG Fuxin, et al. Effect of icing on airfoil with control surface and analysis of aerodynamic parameters[J]. Journal of Shanghai Jiao Tong University, 2017, 51(3):367-373.
[10] PAN J P, LOTH E. Detached eddy simulations for iced airfoils[J]. Journal of Aircraft, 2005, 42(6):1452-1461.
[11] TRAVIN A K, SHUR M L, SPALART P R, et al. Improvement of delayed detached-eddy simulation for LES with wall modelling[EB/OL]. (2006-09-07) [2020-10-21]. https://repository.tudelft.nl/islandora/object/uuid: dbcd7d38-60cb-4107-a6cf-9f4b5dd637a9?collection=research.
[12] XIAO M C, ZHANG Y F, ZHOU F. Numerical study of iced airfoils with horn features using large-eddy simulation[J]. Journal of Aircraft, 2018, 56(1):94-107.
[13] 张恒, 李杰, 龚志斌. 基于IDDES方法的翼型结冰失速分离流动数值模拟[J]. 空气动力学学报, 2016, 34(3):283-288.
[13] ZHANG Heng, LI Jie, GONG Zhibin. Numerical simulation of the stall separated flow around an iced airfoil based on IDDES[J]. Acta Aerodynamica Sinica, 2016, 34(3):283-288.
[14] HU S F, ZHANG C, LIU H, et al. Study on vortex shedding mode on the wake of horn/ridge ice contamination under high-Reynolds conditions[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2019, 233(13):5045-5056.
[15] ANSELL P J, BRAGG M B. Unsteady modes in flowfield about airfoil with horn-ice shape[J]. Journal of Aircraft, 2015, 53(2):475-486.
[16] ANSELL P J, BRAGG M B. Characterization of low-frequency oscillations in the flowfield about an iced airfoil[J]. AIAA Journal, 2014, 53(3):629-637.
[17] MA X Y, SCHRÖDER A. Analysis of flapping motion of reattaching shear layer behind a two-dimensional backward-facing step[J]. Physics of Fluids, 2017, 29(11):115104.
[18] HU S F, ZHANG C, LIU H, et al. IDDES simulation of flow separation on an 3-D NACA23012 airfoil with spanwise ridge ice[C]// 2018 Atmospheric and Space Environments Conference. Atlanta, Georgia, USA: AIAA, 2018: 1-10.
[19] LI G H, FU X, WANG F X. High-resolution multi-code implementation of unsteady Navier-Stokes flow solver based on paralleled overset adaptive mesh refinement and high-order low-dissipation hybrid schemes[J]. International Journal of Computational Fluid Dynamics, 2017, 31(9):379-395.
[20] JAMESON A. Time dependent calculations using multigrid, with applications to unsteady flows past airfoils and wings[C]// 10th Computational Fluid Dynamics Conference. Honolulu, HI, USA: AIAA, 1991: 1-14.
[21] ZHANG C, HU S F, LI Y X, et al. Modal analysis of 3-D iced-airfoil aerodynamics based on proper orthogonal decomposition techniques[C]// AIAA Scitech 2019 Forum. San Diego, California, USA: AIAA, 2019: 1-11.
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