@inproceedings{oai:jaxa.repo.nii.ac.jp:00047327,
 author = {古谷, 元和 and 渡邉, 保真 and 鈴木, 宏二郎 and FURUYA, Motokazu and WATANABE, Yasumasa and SUZUKI, Kojiro},
 book = {宇宙航空研究開発機構特別資料: 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2020オンライン論文集, JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online},
 month = {Feb},
 note = {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2020オンライン (2020年9月28日-30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), Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), The riblet is the surface configuration that has tiny grooves aligned regularly in a flow direction. In a low-speed flow regime, it is known that the riblet can reduce the skin friction drag by up to 10% by manipulating the vortices over the surface. Thanks to the recent rapid advancement in micro-machining technology, putting the riblet over the surface of an aircraft will become practical in the near future. Reduction in the skin-friction drag by the riblet is also expected in the hypersonic flow regime, because the flow speed is essentially low near the bottom of the boundary layer over the surface even in such high-speed flight. However, little amount of studies on the hypersonic riblet have been made so far. In the present study, the flow over the flat plate model with the riblet was experimentally investigated at the Mach 7 hypersonic wind tunnel in the Kashiwa campus, the University of Tokyo. The preliminary results were presented in this paper., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030013006, レポート番号: JAXA-SP-20-008},
 pages = {43--46},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {極超音速におけるリブレットの摩擦抵抗低減効果に関する予備検討},
 volume = {JAXA-SP-20-008},
 year = {2021}
}