翼型失速的非线性动力学特性及其控制

doi:CNKI:11-1929/V.20110726.1650.004

流体力学与飞行力学

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翼型失速的非线性动力学特性及其控制

张家忠¹, 李凯伦¹, 陈丽莺²

1. 西安交通大学能源与动力工程学院,陕西西安 710049;
2. 深圳中广核工程设计有限公司常规岛与公用设施所,广东深圳 518057

收稿日期:2011-04-25 修回日期:2011-05-26 出版日期:2011-12-25 发布日期:2011-12-08
通讯作者: 张家忠 E-mail:jzzhang@mail.xjtu.edu.cn
作者简介:张家忠(1968-) 男,博士,教授,博士生导师。主要研究方向:非线性动力学、气动弹性力学、流动控制。 Tel: 029-82664177 E-mail: jzzhang@mail.xjtu.edu.cn
李凯伦(1983-) 男,博士研究生。主要研究方向:尾迹中漩涡结构的演化过程。 E-mail: likailun@stu.xjtu.edu.cn
基金资助:
教育部新世纪优秀人才支持计划(NCET-07-0685)

Nonlinear Dynamics of Static Stall of Airfoil and Its Control

ZHANG Jiazhong¹, LI Kailun¹, CHEN Liying²

1. School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an 710049, China;
2. CI and BOP Department, China Nuclear Power Design Company Ltd (Shenzhen), Shenzhen 518057, China

Received:2011-04-25 Revised:2011-05-26 Online:2011-12-25 Published:2011-12-08

摘要/Abstract

摘要： 以NACA0012翼型为研究对象,应用CBS(Characteristic-Based Split)有限元方法对翼型绕流流场进行数值模拟,着重对翼型失速现象的动力学机理和特征进行研究。首先给出了静止翼型在不同迎角下流场的瞬时流线图以及静态翼型的迎角-升力系数关系曲线,并且分析出此曲线具有滞后、突跳等典型的非线性动力学特性。其次,基于映射的不动点分岔理论,通过构造映射,发现和证明了静态失速是一种鞍-结分岔现象。进一步,由于鞍-结分岔对外部激励的敏感性,因此对在失速迎角附近翼型做俯仰运动(一类外部激励)的动态失速现象亦进行了研究,通过ALE(Arbitrary Lagrangian-Euler)方法处理了翼型俯仰运动中涉及到的动网格问题并求解流场。数值模拟结果表明,特定的外部激励能够明显地提高升力系数并且有效地延迟失速现象的发生,可以作为一种控制失速的有效方法。

关键词: 翼型, 失速, 分岔, 非线性分析, 漩涡脱落

Abstract: Using the CBS (Characteristic-Based Split) finite element method, this paper studies in detail the nonlinear dynamics of stall of airfoil NACA0012.First, the Instantaneous streamline patterns and the angle of attack lift coefficient curves of flows around the static airfoil are presented, and much attention is paid to the hysteresis and jumping phenomena in the angle of attack lift coefficient curve.Next, on the basis of the fixed point bifurcation theory in the map, by introducing a map into the flow field numerical simulation the static stall is proved numerically to be a kind of saddle-node bifurcation which involves the hysteresis and jumping phenomena. Additionally the dynamic stall of the airfoil is investigated by the ALE (Arbitrary Lagrangian-Euler) method, since the saddle-node bifurcation is sensitive to external excitation, which is the pitching-motion of the airfoil around the stall attack angle.The numerical results show that the specific external excitation could significantly enhance the lift coefficient and effectively delay the stall, and it may be considered a powerful control strategy of stall.

Key words: airfoil, stall, bifurcation, nonlinear analysis, vortex shedding

中图分类号:

V211.4

张家忠, 李凯伦, 陈丽莺. 翼型失速的非线性动力学特性及其控制[J]. 航空学报, 2011, 32(12): 2163-2173.

ZHANG Jiazhong, LI Kailun, CHEN Liying. Nonlinear Dynamics of Static Stall of Airfoil and Its Control[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(12): 2163-2173.

参考文献

[1] Mittal S, Saxena P.Prediction of hysteresis associated with static stall of an airfoil[J]. AIAA Journal, 2000, 38(5): 933-935.

[2] 上官云信,周瑞兴,高永卫,等. 翼型相对厚度对失速分离特性的影响[J]. 空气动力学学报,2000,18(增刊):21-26. Shangguan Yunxin, Zhou Ruixing, Gao Yongwei, et al. The effect of relative thickness of airfoil on stall separate character[J]. Acta Aerodynamica Sinica, 2000, 18 (Supplement): 21-26. (in Chinese)

[3] 李栋,Igor Men'shov,中村佳朗. 薄翼失速翼型前缘分离泡对失速特性的影响[J]. 空气动力学学报,2006,24(3):361-366. Li Dong, Igor Men'shov, Yoshiaki Nakamura. The effect of bubble in leading edge region to the thin airfoil stall[J]. Acta Aerodynamica Sinica, 2006, 24(3): 361-366. (in Chinese)

[4] Ham N D. Aerodynamic loading on a two-dimensional airfoil during dynamic stall[J]. AIAA Journal, 1968, 6 (10): 1927-1934.

[5] McCroskey W J, Pucci S L. Viscous-inviscid interaction on oscillating airfoil in subsonic flow[J]. AIAA Journal, 1982, 20(2):167-174.

[6] McCroskey W J, Carr L W, McAlister K W. Dynamic stall experiments on oscillating airfoils[J]. AIAA Jour-nal, 1976, 14(1): 57-63.

[7] McCroskey W J, Philippe J J. Unsteady viscous flow on oscillating airfoils[J]. AIAA Journal, 1975, 13(1): 71-79.

[8] Carr L W. Progress in analysis and prediction of dynamic stall[J]. Journal of Aircraft, 1988, 25(1): 6-17.

[9] Ekaterinaris J A, Platzer M. Computational prediction of airfoil dynamic stall[J]. Progress in Aerospace Sciences, 1998, 33(11-12): 759-846.

[10] 王友进,闫超,周涛. 不同厚度翼型动态失速涡运动数值研究[J]. 北京航空航天大学学报,2006,32 (2):153-157. Wang Youjin, Yan Chao, Zhou Tao. Numerical investigation of dynamic stall vortex movement of different-thickness airfoils[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(2): 153-157. (in Chinese)

[11] Sarkar S, Venkatraman K. Influence of pitching angle of incidence on the dynamic stall behavior of a symmetric airfoil[J]. European Journal of Mechanics/B Fluids, 2008, 27(3): 219-238.

[12] Witteveen J A S, Sarkar S, Bijl H. Modeling physical uncertainties in dynamic stall induced fluid-structure interaction of turbine blades using arbitrary polynomial chaos[J]. Computers and Structures, 2007, 85(11-14): 866-878.

[13] Gaitonde A L. A dual-time method for two-dimensional unsteady incompressible flow calculations[J]. International Journal for Numerical Methods in Engineering, 1998, 41(6): 1153-1166.

[14] Breuer M, Hnel D. A dual time-stepping method for 3D, viscous, incompressible vortex flows[J]. Computers & Fluids, 1993, 22(4-5):467-484.

[15] Nithiarasu P. An arbitrary Lagrangian Eulerian (ALE) formulation for free surface flows using the characteristic-based split (CBS) scheme[J]. International Journal for Numerical Methods in Fluids, 2005, 48(12):1415-1428.

[16] Zienkiewicz O C, Taylor R L, Nithiarasu P. The finite element method for fluid dynamics[M]. 6th ed. Beijing: World Publishing Corporation, 2009:79-105.

[17] 孙旭, 张家忠. 具有运动边界不可压缩粘性流动的CBS有限元方法[J]. 西安交通大学学报, 2011, 45(1): 99-104. Sun Xu, Zhang Jiazhong. A characteristic based split-FEM scheme for incompressible viscous flow with moving boundaries[J]. Journal of Xi'an Jiaotong University, 2011, 45(1):99-104. (in Chinese)

[18] Lippolis A, Vacca G, Grossman B. Incompressible Navier-Stokes solutions on unstructured grids using a co-volume technique//Lecture Notes in Physics, 1993, 414:270-274.

[19] Johnson A A, Tezduyar T E. Mesh update strategies in parallel finite element computations of flow problems with moving boundaries and interfaces[J]. Computer Methods in Applied Mechanics and Engineering, 1994, 119:73-94.

[20] Mittal S, Saxena P. Hysteresis in flow past a NACA0012 airfoil[J]. Computer Methods in Applied Mechanics and Engineering, 2002, 191: 2179-2189.

[21] 张家忠. 非线性动力系统的运动稳定性、分岔理论及其应用[M]. 西安:西安交通大学出版社, 2010: 96-110. Zhang Jiazhong. Stability and bifurcation of nonlinear dynamic systems and their applications[M]. Xi'an:Xi'an Jiaotong University Press, 2010: 96-110. (in Chinese)

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

翼型失速的非线性动力学特性及其控制

Nonlinear Dynamics of Static Stall of Airfoil and Its Control

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