@inproceedings{oai:jaxa.repo.nii.ac.jp:00036829,
 author = {吉田, 茂雄 and 中野, 欣也 and 塩沢, 信秋 and Yoshida, Shigeo and Nakano, Kinya and Shiozawa, Nobuaki},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {May},
 note = {境界層安定性について超音速風洞試験および数値解析を行った。風洞試験は後退翼モデルについて行った。境界層遷移位置をいくつかの迎え角で観測し、境界層吸気による層流域の拡大も観測した。その結果は超音速層流制御の妥当性を示した。線形安定性理論にもとづいて、境界層安定解析コードを開発し、その妥当性を2次元の境界層について確認した。風洞試験結果のひとつを解析し、擾乱の特性を明らかにした。, Supersonic wind tunnel tests and numerical analyses were carried out on the boundary layer stability. Wind tunnel tests were performed on a swept wing model. Boundary layer transition locations were detected at various angles of attack and extensions of laminar flow regions by boundary layer suction were also observed. Consequently, the validity of supersonic laminar flow control was suggested. And a boundary layer stability analyses code was developed, based on the linear stability theory, and its validity was confirmed for two dimensional boundary layers. Then one of the wind tunnel test cases was analyzed, and characteristics of disturbances were clarified., 資料番号: AA0000440006, レポート番号: NAL SP-31},
 pages = {81--90},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {An experimental and numerical study on the compressible laminar flow control},
 volume = {31},
 year = {1996}
}