@inproceedings{oai:jaxa.repo.nii.ac.jp:00004007,
 author = {澤木, 悠太 and 芳賀, 臣紀 and 保江, かな子 and 澤田, 恵介 and Sawaki, Yuta and Haga, Takanori and Yasue, Kanako and Sawada, Keisuke},
 book = {宇宙航空研究開発機構特別資料: 第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013論文集, JAXA Special Publication},
 month = {Mar},
 note = {第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013 (2013年7月4日-5日. タワーホール船堀), 東京, 45th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2013 (July 4-5, 2013. Tower Hall Funabori), Tokyo, Japan, 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., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062268007, レポート番号: JAXA-SP-13-011},
 pages = {35--40},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {高次精度非構造格子法の比較に関する研究},
 volume = {JAXA-SP-13-011},
 year = {2014}
}