低雷诺数NACA0012平面叶栅流场直接数值模拟

朱海涛; 单鹏

低雷诺数NACA0012平面叶栅流场直接数值模拟

朱海涛,
单鹏

北京航空航天大学能源与动力工程学院,北京 100191

计量
- 文章访问数: 1588
- HTML浏览量: 1
- PDF量: 1182
- 被引次数: 0
出版历程
- 收稿日期: 2012-09-18
- 刊出日期: 2013-02-28

Direct numerical simulation of NACA0012 cascade flow at low Reynolds number

School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 采用具有7阶精度的weighted essentially non-oscillatory(WENO)差分格式,直接求解可压缩二维非定常N-S方程组,研究了NACA0012翼型平面叶栅低雷诺数流动的特征.直接模拟及与文献对比的结果表明:叶栅尾缘涡脱落的形成过程与圆柱绕流涡脱落的形成过程非常相似.平面叶栅尾迹区的2阶统计量与孤立翼型尾迹区的2阶统计量具有相同的分布特征,但前者的强度显著大于后者.周期性的涡脱落不仅在上下翼面形成非定常分离,也使得尾迹区某点的总压发生准周期性的变化.随着栅距的减小,翼型上的平均分离位置向前缘移动;尾迹区某点的总压变化频率及其幅值均显著地增加;而且栅距越小,速度脉动2阶统计量反而越大.
- 直接数值模拟 /
- 低雷诺数 /
- 平面叶栅 /
- 涡脱落 /
- WENO(weighted essentially non-oscillatory)差分格式
Abstract: Low Reynolds number flow field developed around a cascade of NACA0012 was numerically simulated by directly solving the unsteady two-dimensional Navier-Stokes equations through weighted essentially non-oscillatory(WENO) schemes with 7th order accuracy.As compared with references,direct numerical simulation results indicate that vortex-shedding process at the cascade trailing edge is similar to that of flow over a cylinder and the statistical traits of the wake region are similar between cascade flow and single airfoil flow at low Reynolds number,but the former is stronger.The vortex-shedding has a significant impact on the overall flowfield,which forms unsteady separation on the airfoil and makes the total pressure in the wake region vary instantaneously.With the decrease of the pitch,the average separation position moves towards the leading edge;the frequency and amplitude of total pressure in the wake region increase markedly,and the statistics of pulse velocity becomes bigger.
- direct numerical simulation /
- low Reynolds number /
- cascade flow /
- vortex-shedding /
- WENO(weighted essentially non-oscillatory) scheme

HTML

参考文献(18)

[1]	Lissman P.Low Reynolds number airfoils[J].Annual Review of Fluid Mechanics,1983,15:223-239.
[2]	Mueller T J,Batill S M.Experimental studies of separation on a two-dimensional airfoil at low Reynolds numbers[J].AIAA Journal,1982,20(4):457-467.
[3]	王光华,刘宝杰,刘涛,等.翼型近尾迹流动的PIV研究:运动学特性[J].航空动力学报,1999,14(2):119-124. WANG Guanghua,LIU Baojie,LIU Tao,et al.A PIV study of near wake flow of airfoil:PartⅠ kinematic characteristics[J].Journal of Aerospace Power,1999,14(2):119-124.(in Chinese)
[4]	刘宝杰,王光华,高歌.翼型近尾迹流动的PIV研究:动力学机制[J].航空动力学报,1999,14(2):125-130. LIU Baojie,WANG Guanghua,GAO Ge.PIV study of airfoil near wake flow:Part Ⅱ dynamic mechanism[J].Journal of Aerospace Power,1999,14(2):125-130.(in Chinese)
[5]	Tatineni M,Zhong X L.Numerical simulation of unsteady low Reynolds number airfoil aerodynamics[R].AIAA-1997-1929,1997.
[6]	叶建,林国华,邹正平,等.低雷诺数下二维翼型绕流的流场特性分析[J].航空动力学报,2003,18(1):38-45. YE Jian,LIN Guohua,ZOU Zhengping,et al.The analysis of flow around a 2-D airfoil at low Reynolds number[J].Journal of Aerospace Power,2003,18(1):38-45.(in Chinese)
[7]	叶建,邹正平,陆利蓬,等.低雷诺数下翼型前缘流动分离机制的研究[J].北京航空航天大学学报,2004,30(8):693-697. YE Jian,ZOU Zhengping,LU Lipeng,et al.Investigation of separation mechanism for airfoil leading edge flow at low Reynolds number[J].Journal of Beijing University of Aeronautics and Astronautics,2004,30(8):693-697.(in Chinese)
[8]	Farrel C,Adamczyk J.Full potential solution of transonic quasi-three dimension flow through a cascade using artificial compressibility[J].Journal of Engineering for Power,1982,104(1):143-153.
[9]	Bendiksen O O.Euler calculations of unsteady transonic flow in cascades[R].AIAA-91-1104,1991.
[10]	Hsiao C,Bendiksen O. Finite element Euler calculations of unsteady transonic cascade flows[R].AIAA-92-2120,1992.
[11]	Ahmed N,Yilbas B S,Budair M O.Computational study into the flow field developed around a cascade of NACA 0012 airfoils[J].Computer Methods in Applied Mechanics and Engineering,1998,167(1/2):17-32.
[12]	Moin P,Mahesh K.Direct numerical simulation:a tool in turbulence research[J].Annual Review of Fluid Mechanics,1998,30:539-578.
[13]	傅德熏,马延文,李新亮,等.可压缩湍流直接数值模拟[M].北京:科学出版社,2010.
[14]	Wu M,Martin M P.Direct numerical simulation of supersonic turbulent boundary layer over a compression ramp[J].AIAA Journal,2007,45(4):879-889.
[15]	Jiang G S,Shu C W.Efficient implementation of weighted essentially non-oscillatory schemes[J].Journal of Computational Physics,1996,126(1):202-228.
[16]	Gloerfelt X,Lafon P.Direct computation of the noise induced by a turbulent flow through a diaphragm in a duct at low Mach number[J].Computers & Fluids,2008,37(4):388-401.
[17]	叶建.非定常环境中叶片边界层时空演化机制的大涡模拟[R].北京:北京航空航天大学,2008. Ye Jian.Large-eddy simulation of blade boundary layer spatio-temporal evolution under unsteady disturbances[R].Beijing:Beijing University of Aeronautics and Astronautics,2008.(in Chinese)
[18]	童秉刚,张炳暄,崔尔杰.非定常流与涡运动[M].北京:国防工业出版社,1993.