@inproceedings{oai:jaxa.repo.nii.ac.jp:00037237,
 author = {浅井, 雅人 and 清野, 宏 and 伊藤, 信毅 and Asai, Masahito and Seino, Hiroshi and Ito, Nobutake},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Jan},
 note = {30 Sep.-1 Oct. 1997 (21st). 26-27 Mar. 1998 (22nd), 30 Sep.-1 Oct. 1997 (21st). 26-27 Mar. 1998 (22nd), 圧縮性3次元境界層の安定性を線形安定性理論に基づいて調べた。境界層分布として一群のFalkner-Skan-Cooke型分布を用いて、マッハ数M(sub e)がそれぞれ0.2と2.0の亜音速および超音速境界層に対して安定性解析を行った。その結果、最大横流れ速度が外部流れ方向速度の5%を越えると、このふたつのマッハ数において横流れ不安定性が支配的になることがわかった。マッハ数に対する最大不安定モードの伝搬角と位相速度の依存性は、横流れ不安定性においては非常に弱いこともわかった。, Stability of compressible three dimensional boundary layers is examined on the basis of the linearized stability theory. Stability analysis is made for subsonic and supersonic boundary layers at Mach numbers M(sub e) = 0.2 and 2.0 respectively, using a family of the Falkner-Skan-Cooke type profiles as the boundary layer profiles. The results show that the cross flow instability becomes dominant for both the Mach numbers when the maximum cross flow velocity exceeds 5 percent of the external streamwise velocity. It is also shown that the dependency of the propagation angle and phase speed of the most unstable mode on the Mach number is very weak for the cross flow instability., 資料番号: AA0001655014, レポート番号: NAL SP-40},
 pages = {57--58},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {三次元境界層の安定性に対する圧縮性の影響},
 volume = {40},
 year = {1999}
}