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Volume 38 Issue 12
Dec.  2012
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Journal of Beijing University of Aeronautics and Astronautics  > 2012  >  38(12): 1591-1595.
Cui Shuxin, Gao Lin, Gao Geet al. Numerical simulation based on CE/SE method for airfoil flow with shock wave[J]. Journal of Beijing University of Aeronautics and Astronautics, 2012, 38(12): 1591-1595. (in Chinese)
Citation: Cui Shuxin, Gao Lin, Gao Geet al. Numerical simulation based on CE/SE method for airfoil flow with shock wave[J]. Journal of Beijing University of Aeronautics and Astronautics, 2012, 38(12): 1591-1595. (in Chinese)
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Numerical simulation based on CE/SE method for airfoil flow with shock wave

  • School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 14 Sep 2011
  • Publish Date: 30 Dec 2012
    Abstract
  • A new numerical scheme was developed to avoid using double spatial grids to capture shock wave through the original space-time conservation element and solution element (CE/SE) method on the 2-D structured quadrilateral meshes. The design of the new scheme was based on the redefinition of conservation element and solution element as well as one of solution points involving both cell centers and vertices. Numerical simulations for flows around airfoils involving shock wave were implemented using the new scheme in combination with Courant number insensitive scheme(CNIS) and local time-stepping method. The results computed from the modified scheme, comparing with that achieved by the original CE/SE method and an advisory group for aerospace research and development(AGARD) report, show a better resolution of the shock wave and that there is no obvious numerical oscillatory before and after the shock wave. The new scheme provides a more accurate and stable means for computing shock waves in flows over airfoils.

     

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    • References(12)
  • [1]
    Van Leer B.Flux-vector splitting for the Euler equations[J].Lecture Notes in Physics ,1982,170: 507-512
    [2]
    Roe P L.Approximate Riemann solvers,parameter vectors,and difference schemes[J].Journal of Computational Physics,1981,43(2): 357-372
    [3]
    Chang S C.The method of space-time conservation element and solution element—a new approach for solving the navier-stokes and euler equations[J].Journal of Computational Physics,1995,119(2): 295-324
    [4]
    Chang S C.Courant number insensitive CE/SE schemes .AIAA-2002-3890,2002
    [5]
    刘敏,吴克启.基于非结构网格CE/SE算法圆柱绕流气动声场模拟[J].工程热物理学报,2009(2):227-229 Liu Min,Wu Keqi.The aero-acoustics simulation of flow around a cylinder using unstructured CE/SE scheme[J].Journal of Engineering Thermophysics,2009(2):227-229(in Chinese)
    [6]
    凌文辉,赵书苗,刘建文,等.时空守恒CE/SE数值方法在凹槽燃烧流动中的应用研究[J].推进技术,2010(1):34-41 Ling Wenhui,Zhao Shumiao,Liu Jianwen,et al.Numerical investigations of the cavity combustion flow using the CE/SE method[J].Journal of Propulsion Technology,2010(1):34-41(in Chinese)
    [7]
    Ji Z,Zhou Y F.A comparison study of three CESE schemes in MHD simulation[J].Chinese Physics Letters,2010,27(8):085201
    [8]
    孙孔倩,樊未军,杨茂林.CE/SE 法模拟爆震波点火及传播过程[J].航空动力学报,2008,23(2): 244-250 Sun Kongqian,Fan Weijun,Yang Maolin.Numerical simulation of detonation ignition and propagation progress by CE/SE method[J].Journal of Aerospace Power,2008,23(2): 244-250(in Chinese)
    [9]
    崔树鑫,韩玉琪,高歌.二维翼型绕流的CE/SE方法[J].北京航空航天大学学报,2011,37(1): 21-24 Cui Shuxin,Han Yuqi,Gao Ge.Space-time conservation element and solution element method (CE/SE) applied to flows around 2D airfoil[J].Journal of Beijing University of Aeronautics and Astronautics,2011,37(1):21-24(in Chinese)
    [10]
    Zhang Z C,Yu S,Chang S C.A space-time conservation element and solution element method for solving the two-and three-dimensional unsteady Euler equations using quadrilateral and hexahedral meshes[J].Journal of Computational Physics,2002,175(1):168-199
    [11]
    Yen J C,Wagner D A.Computational aeroacoustics using a simplified courant number insensitive CE/SE method .AIAA-2005-2820,2005
    [12]
    Yoshihara H,Sacher P.Test cases for inviscid flow field methods .Advisory Group for Aerospace Research and Development (AGARD)-AR-211,1985
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