@inproceedings{oai:jaxa.repo.nii.ac.jp:00037179,
 author = {小林, 修 and 谷, 泰寛 and 天野, 完一 and 平原, 誠 and Kobayashi, Osamu and Tani, Yasuhiro and Amano, Kanichi and Hirahara, Makoto},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Feb},
 note = {航空宇宙技術研究所 12-13 Jun. 1997 東京 日本, National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan, 遷音速高揚力条件での性能向上のため、新しい翼型設計法を開発した。本手法の主概念は、衝撃波横断圧力差と境界層剥離限界との相関に基づいている。また、逆解法を組込んで設計圧力分布を実現した。本手法を用いて、遷音速高揚力性能を実現する遷音速輸送機翼の翼型を設計した。本報告では、新しい遷音速法3次元翼設計により設計された翼型の適用を試みた。, A new airfoil design method was developed to improve the performance at transonic high lift condition. The main concept of the method is based on the relation between pressure difference across the shock wave and criteria for boundary-layer separation, and an inverse method is also incorporated to realize the designed pressure distribution. An airfoil was designed using this method for transonic transport wing to realize the transonic high lift performance. In this report the application of new airfoil designed here using new transonic method 3-D wing design was conducted., 資料番号: AA0001433053, レポート番号: NAL SP-37},
 pages = {325--330},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {新しい遷音速翼型設計法},
 volume = {37},
 year = {1998}
}