Tohoku University
JAXA's Engineering Digital Innovation Center, Japan Aerospace Exploration Agency (JAXA)(JEDI)
Wind Tunnel Technology Center, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA)
Tohoku University
45th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2013 (July 4-5, 2013. Tower Hall Funabori), Tokyo, Japan
抄録（英）
The inviscid flows over ONERA-M6 wing computed by the spectral volume (SV) and discontinuous Galerkin (DG) methods are compared with that given by the conventional cell-vertex finite volume scheme using the same unstructured tetrahedral grid. In comparison, solution accuracy, and computational cost are critically examined. It is shown that both SV and DG schemes can yield highly resolved shocked flows but their computational costs are substantially higher than that of the conventional finite volume scheme. Laminar boundary layer flow and turbulent flow over 3D flat plate are also computed. In particular, v velocity in laminar flowobtained by DG scheme using hybrid cell grid agree well with the Blasius solution even with less grid resolution.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
高次精度非構造格子法の比較に関する研究
62268007.pdf
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