@inproceedings{oai:jaxa.repo.nii.ac.jp:00005941,
 author = {横川, 譲 and 村山, 光宏 and 山本, 一臣 and 伊藤, 健 and 藤井, 啓介 and Yokokawa, Yuzuru and Murayama, Mitsuhiro and Yamamoto, Kazuomi and Ito, Takeshi and Fujii, Keisuke},
 book = {宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集　第37回・第38回, JAXA Special Publication: Proceedings of the 37th and 38th JAXA Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Feb},
 note = {The results of the wind tunnel testing for a high-lift configuration aircraft model in JAXA are given in this paper. The testing was aiming to store large amount of basic aerodynamic information by various measurement techniques to provide the experimental data for CFD (Computational Fluid Dynamics) validation and to understand flow physics. As a result of the testing, data for forces, moments, pressure distributions, surface flow patterns, transition characteristics were acquired. In addition, measurement techniques, especially PIV (Particle Image Velocimetry), PSP (Pressure Sensitive Paint) and noise survey were advanced., 資料番号: AA0063156022, レポート番号: JAXA-SP-06-013},
 pages = {77--80},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {JAXA高揚力装置模型低速風洞試験について},
 volume = {JAXA-SP-06-013},
 year = {2007}
}