@inproceedings{oai:jaxa.repo.nii.ac.jp:00003252,
 author = {青野, 光 and 立川, 智章 and 安養寺, 正之 and 涌井, 翔太郎 and 濱田, 大生 and Aono, Hikaru and Tatsukawa, Tomoaki and Anyoji, Masayuki and Wakui, Shotaro and Hamada, Daiki},
 book = {宇宙航空研究開発機構特別資料: 第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 49th Fluid Dynamics Conference / the 35th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム (2017年6月28日-30日. 国立オリンピック記念青少年総合センター), 渋谷区, 東京, 49th Fluid Dynamics Conference /the 35th Aerospace Numerical Simulation Symposium (June 28-30, 2017. National Olympics Memorial Youth Center), Shibuya-ku, Tokyo, Japan, This paper conducts two-dimensional numerical flow simulations around an improved Ishii airfoil under low Reynolds number flow conditions. The improved Ishii airfoil is proposed in previous efforts and demonstrated better aerodynamic performance in comparison with those of an original Ishii airfoil. At first, numerical results in the cases of angles of attack ranging from -6 degrees to 9 degrees and a chord-based Reynolds number of 20,000 are compared with the experimental data. Results show a fair agreement with the experimental data. Then, Reynolds number effects are studied for the angles of attack at 3 degrees and 6 degrees, respectively. Numerical results present similar trend to that observed in the experiments. Furthermore, it seems that the change of Reynolds number has certain impact on the aerodynamic coefficients when the laminar separation bubble is not observed over the airfoil., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1730011018, レポート番号: JAXA-SP-17-004},
 pages = {123--126},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {低レイノルズ数条件下での改良型石井翼型の流体計算と性能評価},
 volume = {JAXA-SP-17-004},
 year = {2017}
}