NUMERICAL STUDY ABOUT AERODYNAMIC CHARACTERISTICS AND FLOW FIELD STRUCTURES FOR A SKIN OF AIRFOIL WITH ACTIVE OSCILLATION AT LOWREYNOLDS NUMBER

Liu Qiang; Liu Zhou; Bai Peng; Li Feng

doi:10.6052/0459-1879-15-188

Volume 48 Issue 2

Turn off MathJax

Article Contents

Abstract

References

Chinese Journal of Theoretical and Applied Mechanics > 2016 > 48(2): 269-277. > DOI: 10.6052/0459-1879-15-188 CSTR: 32045.14.0459-1879-15-188

Liu Qiang, Liu Zhou, Bai Peng, Li Feng. NUMERICAL STUDY ABOUT AERODYNAMIC CHARACTERISTICS AND FLOW FIELD STRUCTURES FOR A SKIN OF AIRFOIL WITH ACTIVE OSCILLATION AT LOWREYNOLDS NUMBER[J]. Chinese Journal of Theoretical and Applied Mechanics, 2016, 48(2): 269-277. DOI: 10.6052/0459-1879-15-188

Citation:

PDF (10493 KB)

NUMERICAL STUDY ABOUT AERODYNAMIC CHARACTERISTICS AND FLOW FIELD STRUCTURES FOR A SKIN OF AIRFOIL WITH ACTIVE OSCILLATION AT LOWREYNOLDS NUMBER

China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received Date: May 26, 2015
Revised Date: October 12, 2015

Graphical Abstract

Abstract

Abstract

For the poor aerodynamic performance of airfoil at low Reynolds number, the paper targets the active oscillation for flexible skin of airfoil in order to improve its aerodynamic characteristics and flow field structures.Roe method with preconditioning technique was used to solve the unsteady compressible N-S equations and simulate the flow for NACA4415 airfoil at low Reynolds number.The aerodynamic force characteristics and laminar flow separation structures were compared by time-average and unsteady methods when the skin is static or oscillating.Preliminary studies indicate when the flexible skin actively oscillates with appropriate amplitude and frequency, the time-average lift and drag characteristics increase significantly.The separation bubble structures transform from trailing-edge laminar separation bubble to classic long laminar separation bubble.The separation position moves downstream and the separation region reduces.On this basis, the paper studied the alterations of the unsteady flow structures and pressure coefficient distributions more detailed during one period with the two states of the skin.The flow field structures and the pressure distributions keep steady in the front part of separation region at a static skin.The flow approximates steady separation and the unsteady flow phenomena like Karman vortex streets only appear at the trailing edge.Otherwise, for the oscillating skin, the unsteady vortexes generate near the separation position, subsequently move, and then shed along the airfoil surface.The flow presents unsteady separation and displays a wide range of pressure oscillation.Owing to the oscillating skin, the fluid movements are closer to the wall.The large scale laminar flow separation phenomenon is suppressed apparently.
- low Reynolds number,
- active oscillation,
- numerical simulation,
- aerodynamic characteristics,
- flow field structures

FullText(HTML)

References (20)

References

1 陈广强, 刘强, 石永彬等. 一种临近空间升浮一体飞行器气动布局设计研究. 空气动力学学报, 2015, 33(2):218-224(Cheng Guangqiang, Liu Qiang, Shi Yongbin, et al. Aerodynamic configuration design of a buoyancy-lifting vehicle in the near-space. Acta Aerodynamica Sinica, 2015, 33(2):218-224(in Chinese))

2 Shyy W, Lian Y. Aerodynamics of Low Reynolds Number Flyers. New York:Cambridge University Press, 2008:78-85

3 李锋, 白鹏, 石文等. 微型飞行器低雷诺数空气动力学. 力学进展, 2007, 37(2):257-268(Li Feng, Bai Peng, Shi Wen, et al. Micro air vehicle aerodynamics at low reynolds number. Advances in Mechanics, 2007, 37(2):257-268(in Chinese))

4 白鹏, 李锋, 詹慧玲等. 翼型低Re 小攻角非线性非定常层流分离现象研究. 中国科学:物理学力学天文学, 2015, 45(2):24703-024703(Bai Peng, Li Feng, Zhan Huiling, et al. Study about the non-linear and unsteady laminar separation phenomena around the airfoil at low Reynolds number with low incidence. Sci Sin-Phys Mech Astron, 2015, 45(2):24703-024703(in Chinese))

5 吴鋆, 王晋军, 李天. NACA0012 翼型低雷诺数绕流的实验研究. 实验流体力学, 2013,(6):32-38(Wu Jun, Wang Jinjun,Li Tian. Experimental investigation on low Reynolds number behavior of NACA0012 airfoil. Journal of Experiments in Fluid Mechanics, 2013,(6):32-38(in Chinese))

6 Horton HP. Laminar separation bubbles in two and three dimensional incompressible flow.[PhD Thesis]. London:Queen Mary University of London, 1968

7 Mueller TJ, Batil SM. Experimental studies of separation on a twodimensional airfoil at low Reynolds numbers. AIAA Journal, 1982, 20(4):457-463

8 Kojima R, Nonomura T, Oyama A, et al. Large-eddy simulation of low-Reynolds-number flow over thick and thin NACA airfoils. Journal of Aircraft, 2013, 50(1):187-196

9 白鹏, 崔尔杰, 李锋等. 对称翼型低雷诺数小攻角升力系数非线性现象研究. 力学学报, 2006, 38(1):1-8(Bai Peng, Cui Erjie, Li Feng, et al. Study of the non-linear lift coefficient of the symmetric airfoil at low Reynolds number near the 0ffi angle of attack. Chinese Journal of Theoretical and Applied Mechanics, 2006, 38(1):1-8(in Chinese))

10 Munday D, Jacob J. Active control of separation on a wing with oscillating camber. Journal of Aircraft, 2002, 39(1):187-189

11 郭秋亭. 局部主动变形翼型和折叠翼变形飞机动态气动特性数值模拟研究.[博士论文]. 绵阳:中国空气动力研究与发展中心, 2009:86-89(Guo Qiuting. Numerical simulation of the dynamic aerodynamic characteristics about partial flexible airfoils and folding wing aircraft.[PhD Thesis]. Mianyang:China Aerodynamics Research and Development Center, 2009:86-89(in Chinese))

12 Gross A, Fasel HF. Numerical investigation of separation for airfoils at low reynolds numbers. AIAA Paper No.2010-4736

13 Weiss JM, Smith WA. Preconditioning applied to variable and constant density flows. AIAA Journal, 1995, 33(11):2050-2057

14 Luo H, Baum JD, Lohner R. A fast, matrix-free implicit method for compressible flows on unstructured grids. Journal of Computational Physics, 1998, 146(2):664-690

15 Rong YS, Wei YC. A flux vector splitting scheme for low Mach number flows in preconditioning method. Applied Mathematics & Computation, 2014, 242(1):296-308

16 蒋跃文, 叶正寅, 王刚. 基于非结构网格的高效求解方法研究. 计算力学学报, 2012, 29(2):217-223(Jang Yuewen, Ye Zhengyin, Wang Gang. Efficient solution of Euler/N-S equations on unstructured grids. Chinese Journal of Computational Mechanics, 2012, 29(2):217-223(in Chinese))

17 Shima E, Kitamura K. New approaches for computation of low Mach number flows. Computers & Fluids, 2013, 85(10):143-152

18 Selig MS, Guglielmo JJ. Experimental on airfoils at low Reynolds number. AIAA Paper, AIAA-96-0062

19 刘君, 白晓征, 郭正. 非结构动网格计算方法. 长沙:国防科技大学出版社, 2009:81-85(Liu Jun, Bai Xiaozheng, Guo Zheng. Computational Method for Unstructured Moving Grids. Changsha:National University of Defense Technology Press, 2009:81-85(in Chinese))

20 Katam V, LeBeau RP, Jacob JD. Simulation of separation control on a morphing wing with conformal camber. AIAA Paper No.2005-4880

[1]	Li Shiqing, Cai Shuxuan, Xia Meihua, Luo Zhenbing, Han Yan. NUMERICAL SIMULATION STUDY ON THE FLOW CHARACTERISTICS AROUND FLAT PLATES WITH CONCAVE/CONVEX TREATMENT[J]. Chinese Journal of Theoretical and Applied Mechanics, 2025, 57(5): 1077-1098. DOI: 10.6052/0459-1879-24-495
[2]	Li Heng, Wang Bin, Ye Liuqing, Li Kai, Jin Ke. A LOOSE COUPLING NUMERICAL SIMULATION METHOD BETWEEN FLOW FIELD AND ELECTROMAGNETIC FIELD OF HYPERSONIC VEHICLE[J]. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(6): 1678-1687. DOI: 10.6052/0459-1879-23-514
[3]	Fu Yang’aoxiao, Liu Qingzong, Ding Mingsong, Jiang Tao, Li Peng, Dong Weizhong, Xu Yong, Gao Tiesuo. ANALYSIS OF GAS MODEL’S INFLUENCE ON AERODYNAMIC CHARACTERISTICS FOR HYPERSONIC VEHICLE OVER HOT JET INTERACTION FLOW FIELD[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1229-1241. DOI: 10.6052/0459-1879-21-685
[4]	Yan Chenyi, Chen Ying. NUMERICAL INVESTIGATION ON THE WATER-ENTRY CAVITY FEATURE AND FLOW STRUCTURE OF A SPINNING SPHERE BASED ON LARGE-EDDY SIMULATION[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(4): 1012-1025. DOI: 10.6052/0459-1879-21-634
[5]	Deng Bin, Wang Mengfei, Huang Zongwei, Wu Zhiyuan, Jiang Changbo. NUMERICAL SIMULATION OF THE HYDRODYNAMIC CHARACTERISTICS OF VIOLENT AERATED FLOWS NEAR VERTICAL STRUCTURE UNDER WAVE ACTION[J]. Chinese Journal of Theoretical and Applied Mechanics, 2020, 52(2): 408-419. DOI: 10.6052/0459-1879-20-029
[6]	Xu Bofeng, Liu Bingbing, Feng Junheng, Zuo Lu. INFLUENCE OF VORTEX CORE SIZE ON AERODYNAMIC CALCULATION OF WIND TURBINE IN FREE VORTEX WAKE METHOD[J]. Chinese Journal of Theoretical and Applied Mechanics, 2019, 51(5): 1530-1537. DOI: 10.6052/0459-1879-18-440
[7]	Zhu Zheng, Zhao Qijun, Wang Bo. STUDIES ON VORTEX INTERACTION MECHANISM AND AERODYNAMIC CHARACTERISTIC OF SCISSORS TAIL ROTOR[J]. Chinese Journal of Theoretical and Applied Mechanics, 2016, 48(4): 886-896. DOI: 10.6052/0459-1879-15-338
[8]	Jun Zhou, Youhe Zhou. A new simple method of implicit time integration for dynamic problems of engineering structures[J]. Chinese Journal of Theoretical and Applied Mechanics, 2007, 23(1): 91-99. DOI: 10.6052/0459-1879-2007-1-2006-167
[9]	Z.Y. Gao, Tongxi Yu, D. Karagiozova. Finite element simulation on the mechanical properties of MHS materials[J]. Chinese Journal of Theoretical and Applied Mechanics, 2007, 23(1): 65-75. DOI: 10.6052/0459-1879-2007-1-2006-198
[10]	NUMERICAL ANALYSIS OF FLOW STRUCTURE AROUND A CIRCULAR CYLINDER IN OSCILLATORY FLOW AT LOW Kc NUMBERS[J]. Chinese Journal of Theoretical and Applied Mechanics, 1992, 24(3): 274-282. DOI: 10.6052/0459-1879-1992-3-1995-739

Cited By

Cited by

Periodical cited type(18)

1.	时晓天，张桂茹，吕蒙，赵渊，高军. 结构变形对高超声速可变形减速器的动态稳定性影响分析. 航天返回与遥感. 2025(01): 11-20 .
2.	张鑫，王勋年. 正弦交流介质阻挡放电等离子体激励器诱导流场研究的进展与展望. 力学学报. 2023(02): 285-298 . 本站查看
3.	陈肇麟，陆政旭，肖天航，邓双厚. 局部振动对火星环境下薄翼型气动性能的影响. 北京航空航天大学学报. 2023(11): 2938-2950 .
4.	黄广靖，戴玉婷，杨超. 低雷诺数俯仰振荡翼型等离子体流动控制. 力学学报. 2021(01): 136-155 . 本站查看
5.	李钊，杨广珺，蒋锋. 随积冰历程的机翼蒙皮载荷实验研究. 实验流体力学. 2021(03): 9-15 .
6.	阳鹏宇，张鑫，赖庆仁，车兵辉，陈磊. 机翼尺度效应对等离子体分离流动控制特性的影响. 力学学报. 2021(12): 3321-3330 . 本站查看
7.	马东立，张良，杨穆清，夏兴禄，王少奇. 超长航时太阳能无人机关键技术综述. 航空学报. 2020(03): 34-63 .
8.	刘惠祥，何国毅，王琦. 蜻蜓滑翔时柔性褶皱前翅气动特性分析. 力学学报. 2019(01): 94-102 . 本站查看
9.	赵炜，高德亮，黄江流，尹航，周俊忠. 低雷诺数下速度对流场结构的影响研究. 沈阳航空航天大学学报. 2019(06): 14-21 .
10.	李冠雄，马东立，杨穆清，郭阳. 低雷诺数翼型局部振动非定常气动特性. 航空学报. 2018(01): 118-130 .
11.	李国强，张卫国，陈立，聂博文，张鹏，岳廷瑞. 风力机叶片翼型动态试验技术研究. 力学学报. 2018(04): 751-765 . 本站查看
12.	于晓东，袁腾飞，李代阁，曲航，郑旭航. 极端工况双矩形腔静压推力轴承动态特性. 力学学报. 2018(04): 899-907 . 本站查看
13.	李国强，陈立，黄霞. 横摆振荡翼型动态气动掠效应试验研究. 力学学报. 2018(05): 977-989 . 本站查看
14.	刘强，刘强，白鹏，李锋. 不同雷诺数下翼型气动特性及层流分离现象演化. 航空学报. 2017(04): 27-39 .
15.	王人凤，尤云祥，陈科，段金龙. 两自由度舵-轴系统振动三维效应修正模型. 力学学报. 2017(04): 920-928 . 本站查看
16.	朱玉杰，孙振生，张炜，张世英. 低Reynolds数翼型绕流主动控制技术. 气体物理. 2017(06): 18-27 .
17.	朱正，招启军，王博. 剪刀式尾桨涡流干扰机理和气动特性研究. 力学学报. 2016(04): 886-896 . 本站查看
18.	王睿，熊鹰，王展智. 混合式CRP面元法计算对比. 力学学报. 2016(06): 1425-1436 . 本站查看

Other cited types(8)

Get Citation

PDF

XML

Article Metrics

Article views (1749) PDF downloads (1631) Cited by(26)

NUMERICAL STUDY ABOUT AERODYNAMIC CHARACTERISTICS AND FLOW FIELD STRUCTURES FOR A SKIN OF AIRFOIL WITH ACTIVE OSCILLATION AT LOWREYNOLDS NUMBER