@inproceedings{oai:jaxa.repo.nii.ac.jp:00038100,
 author = {杉浦, 裕樹 and 高木, 正平 and 徳川, 直子 and 西沢, 啓 and Sugiura, Hiroki and Takagi, Shohei and Tokugawa, Naoko and Nishizawa, Akira},
 book = {航空宇宙技術研究所特別資料: 第28回境界層遷移の解明と制御研究会講演論文集, Special Publication of National Aerospace Laboratory: Proceedings of the 28th NAL Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Jan},
 note = {Transition on the natural laminar flow wing of a non-powered scaled supersonic experimental airplane was measured by hot-film sensors and an infrared camera at Mach 2. In order to supress crossflow instability which dominates the transition on the highly swept wing, the pressure falls very rapidly in the vicinity of leading edge of the wing, so as to minimize the crossflow velocity components. The unit Reynolds number had no effect on the transition Reynolds numbers of the wing. The transition Reynolds number was 0.8 million at 70 percent semi-spanwise location at Mach 2 at the angle of attack of 2 deg. Transition location in flight was estimated by conducting transition measurement in a quiet low Reynolds number wind tunnel and in a variable unit Reynolds number wind tunnel which has moderately low turbulence. The transition at 70 percent semi-spanwise position at the angle of attack of 2 deg at Mach 2 in flight was predicted to be located downstream of 60 percent chordwise position., 資料番号: AA0032827008, レポート番号: NAL SP-54},
 pages = {27--30},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {マッハ2における小型超音速実験機の遷移特性},
 volume = {54},
 year = {2002}
}