@inproceedings{oai:jaxa.repo.nii.ac.jp:00014351,
 author = {浅井, 圭介 and 永井, 大樹 and 沼田, 大樹 and 安養寺, 正之 and 伊田, 真悟 and 野瀬, 慶 and Asai, Keisuke and Nagai, Hiroki and Numata, Daijyu and Anyoji, Masayuki and Ida, Shingo and Nose, Kei},
 book = {宇宙航行の力学シンポジウム: 平成22年度, Symposium on Flight Mechanics and Astrodynamics: 2010},
 month = {Aug},
 note = {宇宙航行の力学シンポジウム 平成22年度 (2010年12月16-17日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Symposium on Flight Mechanics and Astrodynamics,  2010 (December 16-17, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The aerodynamic charactetistics of a 5% flat plate and an NACA0012-34 airfoil in low Reynolds number (Re=0.43x10(exp 4)-4.1x10(exp 4)) and high subsonic flow (M=0.1-0.65) were investigated in the Mars Wind Tunnel (MWT) at Tohoku University. A two-component balance system and Pressure-Sensitive Paint (PSP) technique have been developed to measure the lift and drag forces and pressure profiles on the models. For the flat plate, Mach number effect does not have much effect on its aerodynamic performance while Reynolds number affects the lift slope and the drag characteristics. On the contrary, for the NACA00121-34 airfoil, both Reynolds and Mach number effects become more prominent. The lift curve is highly nonlinear and the drag polar is affected by behaviors of a laminar separation bubble. It was suggested that Mach number has efects to delay transition of the shear layer from laminar to turbulent state., 資料番号: AA0065106032},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {火星大気風洞における低レイノルズ数翼型実験},
 year = {2011}
}