@article{oai:jaxa.repo.nii.ac.jp:00021695,
 author = {石川, 敬掲 and 徳川, 直子 and 上田, 良稲 and 伊藤, 啓吾 and 吉田, 憲司 and Ishikawa, Hiroaki and Tokugawa, Naoko and Ueda, Yoshine and Ito, Keigo and Yoshida, Kenji},
 issue = {2},
 journal = {日本航空宇宙学会論文集, Journal of the Japan Society for Aeronautical and Space Sciences},
 month = {Apr},
 note = {A natural laminar flow wing was designed using a computational-fluid-dynamics-based inverse design method of supersonic transport at high-Reynolds number condition to reduce the friction drag of a large supersonic commercial transport. Design of the higher Reynolds number condition is more difficult than the lower Reynolds number condition because a target pressure distribution that can achieve natural laminar flow has steeper pressure gradients at the leading edge than a low Reynolds number condition. This study improved the conventional natural laminar flow design method by inverse design starting from a low-Reynolds number condition design, variable smoothing strength, the modified trailing edge closing method, and so on. The improved inverse design method was applied to a large supersonic transport with 300 passengers at the condition of Mach 2.0 and high Reynolds number of approximately 126 million based on the mean aerodynamic chord. The results and the effects of the improved natural laminar flow design are described here in., 形態: 図版あり, Physical characteristics: Original contains illustrations, 資料番号: DS1640008005},
 pages = {113(31)--122(40)},
 title = {高レイノルズ数超音速自然層流翼に対する逆問題設計システムの構築},
 volume = {64},
 year = {2016}
}