圆弧翼型跨声速流动的动态模态分析

doi:10.13700/j.bh.1001-5965.2018.0468

摘要
图/表
参考文献
相关文章 (1)

全文: PDF (3366 KB) [HTML] ( )
输出: BibTeX | EndNote (RIS)

摘要跨声速翼型的激波周期性自激振荡会给机翼结构带来附加的脉动载荷，从而加剧飞行器表面结构的疲劳损伤。使用动态模态分解（DMD）方法研究了跨声速下绕厚度18%的对称双圆弧翼型的压力脉动场，分析了DMD提取的各阶主模态的频率特征、压力脉动的空间分布以及压力脉动随激波振荡的时间演化过程，并使用DMD模态进行流场重构。结果表明，DMD方法能准确捕捉流场各特征频率的模态，第1阶模态是激波抖振的主频，在激波的自激振荡过程中占主导作用，前7阶模态重构的流场损失函数降低至4%以内，误差主要分布于激波间断处。

	服务

	把本文推荐给朋友
	加入我的书架
	加入引用管理器
	E-mail Alert
	RSS
	作者相关文章
	胡万林
	于剑
	刘宏康
	阎超

关键词 ：跨声速流动, 自激振荡, 动态模态分解(DMD), 圆弧翼型, 流场重构

Abstract：The periodic self-oscillation of the shock wave of the transonic airfoil will bring additional oscillating loads to the wing structure, thereby aggravating the fatigue damage of the aircraft structure. The dynamic mode decomposition (DMD) method is used to study the pressure fluctuation field of a symmetric circular-arc airfoil with a thickness of 18% around the transonic speed. The frequency characteristics of the main modes of DMD, the spatial distribution of pressure fluctuation and the time evolution of pressure fluctuation with shock wave motion are analyzed, and then DMD mode are used for flow field reconstruction. The results show that the DMD method can accurately capture the mode of each characteristic frequency of the flow field, and the first-order mode is the dominant frequency of the buffeting of the shock wave, which plays a dominant role in the self-oscillation process of the shock wave. The flow field loss function of the first seven modes is reduced within 4%, and the error is mainly distributed in the shock wave discontinuity area.

Key words： transonic flow self-oscillation dynamic mode decomposition (DMD) circular-arc airfoil flow field reconstruction

收稿日期: 2018-08-10

PACS:

V211.3

基金资助:国家自然科学基金（11721202，11402016）

通讯作者: 阎超.E-mail:yanchao@buaa.edu.cn E-mail: yanchao@buaa.edu.cn

作者简介: 胡万林男,硕士研究生。主要研究方向:计算流体力学、流动控制;阎超男,博士,教授,博士生导师。主要研究方向:计算流体力学。

引用本文:

胡万林, 于剑, 刘宏康, 阎超. 圆弧翼型跨声速流动的动态模态分析[J]. 北京航空航天大学学报, 2019, 45(5): 1026-1032.
HU Wanlin, YU Jian, LIU Hongkang, YAN Chao. Dynamic modal analysis of circular-arc airfoil transonic flow. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2019, 45(5): 1026-1032.

链接本文:

http://bhxb.buaa.edu.cn/CN/10.13700/j.bh.1001-5965.2018.0468 或 http://bhxb.buaa.edu.cn/CN/Y2019/V45/I5/1026

[1] 张伟伟,高传强,叶正寅.机翼跨声速抖振研究进展[J].航空学报,2015,36(4):1056-1075.ZHANG W W,GAO C Q,YE Z Y.Research advances of wing/airfoil transic buffet[J].Acta Aeronautica et Astronautica Sinica,2015,36(4):1056-1075(in Chinese).
[2] MCDEVITT J B,LEVY J R,DEIWERT G S.Transonic flow about a thick circular-arc airfoil[J].AIAA Journal,1976,14(5):606-613.
[3] TIJDEMAN H,SEEBASS R.Transonic flow past oscillating airfoils[J].Annual Review of Fluid Mechanics,1980,12:181-222.
[4] LEE B.Self-sustained shock oscillations on airfoils at transonic speeds[J].Progress in Aerospace Sciences,2001,37(2):147-196.
[5] JACQUIN L,MOLTON P,DECK S,et al.Experimental study of shock oscillation over a transonic supercritical profile[J].AIAA Journal,2009,47(9):1985-1994.
[6] HARTMANN A,KLAAS M.Time-resolved stereo PIV measurements of shock-boundary layer interaction on a supercritical airfoil[J].Experiments in Fluids,2012,52(3):591-604.
[7] CHUNG I,LEE D,REU T.Prediction of transonic buffet onset for an airfoil with shock induced separation bubble using steady Navier-Stokes solver:AIAA-2002-2934[R].Reston:AIAA,2002.
[8] XIAO Q,TSAI H M,LIU F.Numerical study of transonic buffet on a supercritical airfoil[J].AIAA Journal,2006,44(3):620-628.
[9] XIONG J T,LIU F,LUO S J.Computation of NACA0012 airfoil transonic buffet phenomenon with unsteady Navier-Stokes equations:AIAA-2012-0699[R].Reston:AIAA,2012.
[10] CHEN L W,XU C Y,LU X Y.Numerical investigation of the compressible flow past an aerofoil[J].Journal of Fluid Mechanics,2010,643(3):97-126.
[11] ROWLEY C W,COLONIUS T,MURRAY R M,et al.Proper orthogonal decomposition of 2D compressible DNS of the flow over a rectangular cavity[C]//Division of Fluid Dynamics Meeting,1999.
[12] SCHMID P J.Dynamic mode decomposition of numerical and experimental data[J].Journal of Fluid Mechanics,2010,656(10):5-28.
[13] 潘翀,陈皇,王晋军.复杂流场的动力学模态分解[C]//第八届全国实验流体力学学术会议论文集.广州:中国科学院南海海洋研究所,2010:77-82.PAN C,CHEN H,WANG J J.Dynamical mode decomposition of complex flow field[C]//8th National Conference on Experimental Fluid Mechanics.Guangzhou:South China Sea Institute of Oceanology,2010:77-82(in Chinese).
[14] LIU H K,YAN C,ZHAO Y T,et al.Analysis of pressure fluctuation in transonic cavity flows using modal decomposition[J].Aerospace Science & Technology,2018,77:819-835.
[15] 寇家庆,张伟伟,高传强.基于POD和DMD方法的跨声速抖振模态分析[J].航空学报,2016,37(9):2679-2689.KOU J Q,ZHANG W W,GAO C Q.Modal analysis of transonic buffet based on POD and DMD method[J].Acta Aeronautica et Astronautica Sinica,2016,37(9):2679-2689(in Chinese).
[16] SPEZIALE C G,ABID R,ANDERSON E C.Critical evaluation of two-equation models for near-wall turbulence[J].AIAA Jornal,1992,30(2):324-331.
[17] SPALART P R,DECK S,SHUR M L,et al.A new version of detached-eddy simulation,resistant to ambiguous grid densties[J].Theoretical and Computational Fluid Dynamics,2006,20:181-195.
[18] VAN LEER B.Towards the ultimate conservative difference scheme.V.A second-order sequel to Godunov's method[J].Journal of Computational Physics,1979,32(1):101-136.
[19] YOON S,JAMESON A.Lower-upper symmetric-Gauss-Seidel method for the Euler and Navier-Stokes equations[J].AIAA Journal,1988,26(9):1025-1026.
[20] JAMESON A.Time dependent calculations using multigrid with applications to unsteady flows past airfoils and wings:AIAA 1991-1596[R].Reston:AIAA,1991.
[21] ROWLEY C W,MEZI C,BAGHERI S,et al.Spectral analysis of nonlinear flows[J].Journal of Fluid Mechanics,2009,641(1):115-127.
[22] CHEN K K,TU J H,ROWLEY C W.Variants of dynamic mode decomposition:Boundary condition,Koopman,and Fourier analyses[J].Journal of Nonlinear Science,2012,22(6):887-915.
[23] JOVANOVIC M R,SCHMID P J,NICHOLS J W.Sparsity-promoting dynamic mode decomposition[J].Physics of Fluids,2014,26(2):561-571.