基于旋转坐标系的高阶间断有限元方法非定常湍流数值模拟
CSTR:
作者:
作者单位:

1.南京航空航天大学航空学院,南京,210016;2.中国空气动力研究与发展中心,绵阳,621000

通讯作者:

吕宏强,教授,博士生导师,E-mail: hongqiang.lu@nuaa.edu.cn。

中图分类号:

V211.3

基金项目:

国家高技术研究发展计划(“八六三”计划) 2015AA015303;国家自然科学基金 11272152;航空基金 20152752033;气动噪声控制重点实验室开放课题资助项目国家高技术研究发展计划(“八六三”计划)(2015AA015303)资助项目;国家自然科学基金(11272152)资助项目;航空基金(20152752033)资助项目;气动噪声控制重点实验室开放课题资助项目。


Numerical Simulations of Turbulent Flow Based on Rotating Reference Frame Using High-Order Discontinuous Galerkin Method
Author:
Affiliation:

1.College of Aerospace Engineering, Nanjing University of Aeronautics & Astronautics, Nanjing, 210016, China;2.China Aerodynamics Research and Development Center, Mianyang, 621000, China

  • 摘要
  • | |
  • 访问统计
  • |
  • 参考文献 [20]
  • |
  • 相似文献 [20]
  • | | |
  • 文章评论
    摘要:

    基于高阶间断有限元方法(Discontinuous Galerkin method,DGM), 对旋转非惯性系下耦合了修正的一方程S-A模型的RANS方程进行了离散求解。为了在稀疏网格上获得更贴近真实的物面形状,使用了多层高阶弯曲网格方法对物面进行拟合。非定常时间推进采用了隐式双时间步方法,每个时间步产生的线性系统采用预处理的方法,即广义最小残差方法(Generalized minimal residual method,GMRES)来求解。计算了旋转圆柱绕流以及经典翼型振荡算例的升力和力矩迟滞曲线,与实验结果以及前人的计算结果对比验证了本文方法的正确性和有效性。

    Abstract:

    The RANS equations coupled with modified S-A model in a rotating reference frame are solved using the high-order discontinuous Galerkin method (DGM). In order to obtain more accurate wall boundaries on relatively coarse grids, a multilevel high-order curved mesh method is employed. An implicit dual time stepping method is adopted for the unsteady simulation, while generalized minimal residual method (GMRES) is deployed to solve the large linear system generated in each time step. The lift and moment hysteresis curves of rotating cylinder flow and classical airfoil oscillation are calculated. The correctness and validity of the proposed method are verified by comparing with the experimental results and previous calculation results.

    参考文献
    [1] 李媛, 康顺. 振荡翼型非定常气动特性数值模拟[J]. 工程热物理学报, 2012, 33(9): 1505-1508.
    [2] 张正秋, 邹正平, 刘火星. 振荡翼型非定常流动数值模拟研究[J]. 燃气涡轮试验与研究, 2009, 22(3): 1-8.
    [3] 程苏堃,杨小权,杨爱明.基于时间谱方法的振荡翼型非定常黏性绕流数值模拟[J].空气动力学学报,2013,31(5): 670-675
    [4] 肖中云. 旋翼流场数值模拟方法研究[D]. 绵阳:中国空气动力研究与发展中心, 2007.
    [5] WANG Z J. High-order methods for the Euler and Navier-Stokes equations on unstructured grids[J]. Progress in Aerospace Sciences, 2007, 43(1/2/3): 1-41.
    [6] BASSI F, REBAY S. High-order accurate discontinuous finite element solution of the 2D Euler equations [J]. Journal of Computational Physics, 1997, 138(2): 251-285.
    [7] 秦望龙, 吕宏强, 伍贻兆. 基于混合网格的高阶间断有限元黏流数值解法[J]. 力学学报, 2013, 45(6): 987-991.
    [8] 秦望龙, 吕宏强, 伍贻兆. 弯曲网格上的间断有限元湍流数值解法研究[J]. 空气动力学学报, 2014, 32(5): 581-586.
    [9] GHOSH A R. Solutions to three-dimensional thin-layer Navier-Stokes equations in rotating coordinates for flow through turbomachinery[D]. Stackville, Mississippi: Mississippi State University,1997.
    [10] CHEN J, GHOSH A, SREENIVAS K, et al. Comparison of computations using Navier-Stokes equations in rotating and fixed coordinates for flow through turbomachinery[C]// Aerospace Sciences Meeting and Exhibit. Reno, NV:[s.n.], 2013.
    [11] AGARWAL R K, DEESE J E. Euler calculations for flowfield of a helicopter rotor in hover[J]. Journal of Aircraft, 1987, 24(4): 231-238.
    [12] 易家训. 流体力学与应用数学讲座[M]. 北京:科学出版社, 1983.
    [13] BLAZEK J. Computational fluid dynamics: Principles and applications[M]. [S.l.]: Elsevier, 2005.
    [14] ZHONG B, QIN N. Non-inertial multiblock Navier-Stokes calculation for hovering rotor flowfields using relative velocity approach[J]. The Aeronautical Journal, 2001,105(1049): 379-389.
    [15] BASSI F, SAVINI M L, REBAY S, et al. Discontinuous Galerkin solution of the Reynolds-averaged Navier-Stokes and k- turbulence model equations[J]. Computer & Fluids, 2005,34(4/5): 507-540.
    [16] MODISETTE J M. An output-based adaptive and high-order method for a rotor in hover[D]. Cambridge, Massachusetts:Massachusetts Institute of Technology, 2008.
    [17] BURGESS N K. An adaptive discontinuous galerkin solver for aerodynamic flows[D].[S.l.]: University of Wyoming, 2011.
    [18] COUTANCEAU M, MENARD C. Influence of rotation on the near-wake development behind an impulsively started circular cylinder[J]. Journal of Fluid Mechanics, 1985, 158: 399-446.
    [19] LANDON R H. NACA0012 oscillation and transient pitching:AGARD-R- 702[R].[S.l.]Compendium of Unsteady Aerodynamic Measurements 1982.
    [20] DEBONIS J R, SCOTT J N. Study of the error and efficiency of numerical schemes for computational aeroacoustics[J]. AIAA Journal, 2002, 40(2): 227-234.
    引证文献
引用本文

张涛,吕宏强,秦望龙,陈正武.基于旋转坐标系的高阶间断有限元方法非定常湍流数值模拟[J].南京航空航天大学学报,2019,51(4):474-485

复制
分享
文章指标
  • 点击次数:
  • 下载次数:
  • HTML阅读次数:
  • 引用次数:
历史
  • 收稿日期:2017-10-16
  • 最后修改日期:2018-03-12
  • 在线发布日期: 2019-10-08
文章二维码
您是第6568779位访问者
网站版权 © 南京航空航天大学学报
技术支持:北京勤云科技发展有限公司
请使用 Firefox、Chrome、IE10、IE11、360极速模式、搜狗极速模式、QQ极速模式等浏览器,其他浏览器不建议使用!