@inproceedings{oai:jaxa.repo.nii.ac.jp:00037100,
 author = {越岡, 康弘 and 谷, 泰寛 and 吉田, 茂雄 and Koshioka, Yasuhiro and Tani, Yasuhiro and Yoshida, Shigeo},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Dec},
 note = {航空宇宙技術研究所 26-28 Mar. 1997 東京 日本, National Aerospace Laboratory 26-28 Mar. 1997 Tokyo Japan, 超音速境界層安定性および遷移予測に関する風洞試験と安定性解析を行った。後退角が45度および65度の後退翼モデルについて風洞試験を行った。遷移現象を明らかにするために、境界層安定性解析コードを線形安定性理論および波束法に基づいて開発した。圧縮性境界層内の3次元擾乱の成長を解析により示した。, Wind tunnel tests and stability analyzes were carried out on supersonic boundary layer stability and transition prediction. Wind tunnel tests were performed on a swept wing model, which has 45 and 65 degrees of sweep angle. To clarify transition phenomena, a boundary layer stability analysis code was developed based on the linear stability theory and wave packet method. The growth of three dimensional disturbance in the compressible boundary layer was shown by analyzes., 資料番号: AA0001320010, レポート番号: NAL SP-36},
 pages = {37--40},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {超音速境界層:安定性と遷移予知},
 volume = {36},
 year = {1997}
}