@techreport{oai:jaxa.repo.nii.ac.jp:00041405,
 author = {杉浦, 裕樹 and 吉田, 憲司 and 徳川, 直子 and 高木, 正平 and 西沢, 啓 and Sugiura, Hiroki and Yoshida, Kenji and Tokugawa, Naoko and Takagi, Shohei and Nishizawa, Akira},
 month = {Dec},
 note = {航空宇宙技術研究所 27-29 Sept.2000 東京 日本, National Aerospace Laboratory 27-29 Sept.2000 Tokyo Japan, 超音速輸送機を目的とした無推力実験機の自然層流翼上の遷移測定をマッハ数2.0と1.2で行った。翼弦沿いに設置した熱フィルム流速計に対する出力信号の振幅中の摂動増加が層流から乱流境界層への遷移を示す。熱フィルム流速計およびPreston管による測定結果は遷移点が翼の半弦の下流に位置していることを明らかにした。, Transition measurement on the natural laminar flow wing of non-powered experimental airplane for supersonic transport was conducted at Mach 2.0 and 1.2. Increase of perturbation in amplitude of output signals for hot-films placed along the wing chord indicates transition from laminar to turbulent boundary layer. Results by hot-film and Preston tubes proved that transition point is located downstream of the half chord of the wing., 資料番号: AA0028637019, レポート番号: NAL SP-48T},
 title = {Transition measurement on the natural laminar flow wing of the non-powered experimental airplane for supersonic transport},
 year = {2000}
}