@inproceedings{oai:jaxa.repo.nii.ac.jp:00048384,
 author = {貝原, 涼弥 and 黒瀬, 章弘 and 河内, 俊憲 and KAIHARA, Ryoya and KUROSE, Akihiro and KOCHI, Tosinori},
 book = {宇宙航空研究開発機構特別資料: 第53回流体力学講演会/第39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 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第53回流体力学講演会/第39回航空宇宙数値シミュレーション技術シンポジウム (2021年6月30日-7月2日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議), The 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium (June 30 - July 2, 2021. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), We constructed a suction-type supersonic wind tunnel to obtain accurate and high-spatial resolution data, mainly velocity data hopefully including wall shear stress, of shock-wave boundary layer interaction (SWBLI) at a high-Reynolds number condition. The wind tunnel had 50 mm-width and height at the exit of the nozzle, and the length of the test section was 800 mm. The nozzle designed Mach number was 2. One of the walls of the test section was diverging by 0.8 deg to cancel the displacement of the developing boundary layer on the wall. To confirm whether the wind tunnel is suitable for the SWBLI experiments at a high-Reynolds number condition, we measured the velocity data in the boundary layer at 697-mm downstream from the nozzle exit by using the Pitot pressure measurement and evaluated Reynolds number based on the momentum thickness and freestream value. The Reynolds number was about 14,000, which barely reached our target value. However, the velocity data near the wall has the problem, and we need to improve in the future., 形態: 図版あり, Physical characteristics: Original contains illustrations, 資料番号: AA2130027011, レポート番号: JAXA-SP-21-008},
 pages = {141--147},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Reθ=14,000の超音速風洞壁に発達する乱流境界層の平均速度計測},
 volume = {JAXA-SP-21-008},
 year = {2022}
}