@inproceedings{oai:jaxa.repo.nii.ac.jp:00005931,
 author = {徳川, 直子 and 吉田, 憲司 and 上田, 良稲 and Tokugawa, Naoko and Yoshida, Kenji and Ueda, Yoshine},
 book = {宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集　第37回・第38回, JAXA Special Publication: Proceedings of the 37th and 38th JAXA Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Feb},
 note = {The experimental validation of natural laminar flow wing designed with the original CFD (Computational Fluid Dynamics)-based inverse design method is carried out by the flight test of an unmanned and scaled supersonic experimental airplane. It is the first challenge to apply the natural laminar flow wing concept to a supersonic vehicle. The concept of natural laminar flow wing is validated by measuring the surface pressure and the transition location. In this paper, the transition characteristics detected by the hot-film sensors and dynamic pressure transducers are briefly introduced. To classify the transition location objectively, a quantity, called 'transition level', is newly introduced. The transition location detected experimentally is in good agreement with numerically predicted location, and the natural laminar flow effect is confirmed at the design condition., 資料番号: AA0063156012, レポート番号: JAXA-SP-06-013},
 pages = {39--42},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {小型超音速実験機の遷移計測:速報},
 volume = {JAXA-SP-06-013},
 year = {2007}
}