@inproceedings{oai:jaxa.repo.nii.ac.jp:00036911,
 author = {桑原, 邦郎 and Kuwahara, Kunio},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Jan},
 note = {航空宇宙技術研究所 6-7 JUN. 1996 東京 日本, National Aerospace Laboratory 6-7 JUN. 1996 Tokyo Japan, ナビエ・ストークス方程式を解いて高レイノルズ非圧縮性流のシミュレーションを行った。乱流モデルを使わずに3次風上差分法を適用し、また多重方向のスキームも用いた。翼まわりの数値計算でで未解決問題に着手し、数値計算研究法の可能性を大幅に広げる新たな結果を紹介した。同じ研究法を用いて、負の厚さの翼の概念を導入し、この概念の適用を提案した。, Incompressible high-Reynolds-number flow are simulated by solving the Navier-Stokes equations. A finite-difference method with third-order upwinding are employed without using any turbulence model. Also multi-directional method is used. Unsolved problems in computation around an airfoil are attacked and new results are presented, which will make the possibility of computational approach widen substantially. Using the same approach, a concept of an airfoil of negative thickness is introduced. Application of this concept is suggested., 資料番号: AA0000685052, レポート番号: NAL SP-34},
 pages = {295--300},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {Simulation of subsonic flow past an airfoil},
 volume = {34},
 year = {1997}
}