@inproceedings{oai:jaxa.repo.nii.ac.jp:00005535,
 author = {菊地, 聡 and 小里, 泰章 and 今尾, 茂樹 and 三井, 浩之 and Kikuchi, Satoshi and Kozato, Yasuaki and Imao, Shigeki and Mitsui, Hiroyuki},
 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40回, JAXA Special Publication: Proceedings of the 40th JAXA Workshop on Investigation and Control of Boundary-Layer Transition},
 month = {Feb},
 note = {Flow characteristics around aerofoil for wing in ground effect are studied experimentally in a wind tunnel. Lift and drug forces were measured directly by three-component force transducer and velocity distributions around the aerofoil were obtained by PIV (Particle Image Velocimetry). Experimental results show that lift and drag forces were consistent with the data obtained earlier qualitatively. With decreasing a ground clearance, the stagnation point moves backward and the effective angle of attack increases. For this reason, the flow rate between the aerofoil and the ground decreases, and the flow between the aerofoil and the ground is decelerated, and the pressure on the undersurface of the aerofoil increases. This is one of the causes of the wing in ground effect., 資料番号: AA0063908014, レポート番号: JAXA-SP-07-026E},
 pages = {45--46},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {The velocity distribution around aerofoil for wing in ground effect},
 volume = {JAXA-SP-07-026E},
 year = {2008}
}