@inproceedings{oai:jaxa.repo.nii.ac.jp:00004022,
 author = {大竹, 智久 and 互井, 梨絵 and 神田, 翔 and 村松, 旦典 and 本橋, 龍郎 and Ohtake, Tomohisa and Tagai, Rie and Kanda, Shou and Muramatsu, Akinori and Motohashi, Tatsuo},
 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, Flow visualization of Ishii airfoil was performed to clarify flow field around the airfoil at chord based Reynolds number from 20,000 to 60,000. Although oil flow technique, one of common and traditional wall tracing visualization methods, was applied to visualize flow field on the airfoil, the flow field could not be visualized clearly in these low Reynolds number region. We devised and applied a new technique of visualizing the flow field on the airfoil surface with fluorescence aqueous; we named this technique as “fluorescence liquid film technique.” This technique is possible to visualize flow field on the airfoil in low Reynolds number regions. As the results of flow visualization by fluorescence liquid film technique, we recognized flow field phenomena on the airfoil in low Reynolds number region that the positions of separation point and reattachment point and the length of separation bubble were changed on the airfoil depending on Reynolds number changing., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062268022, レポート番号: JAXA-SP-13-011},
 pages = {121--125},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {低Re 数におけるIshii 翼型まわりの流れ場},
 volume = {JAXA-SP-13-011},
 year = {2014}
}