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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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