University of Electro-Communications Graduate School
University of Electro-Communications Department of Mechanical Engineering and Intelligent Systems
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2002論文集
雑誌名(英)
Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002
巻
57
ページ
274 - 279
発行年
2003-03
抄録（英）
Supersonic free shear flows including near and far fields were calculated by three dimensional direct numerical simulations with shock capturing compact schemes. Mechanism of sound wave emission was investigated in a transitional plane jet. Results from DNS are presented for Mc = 1.17 and Mc = 1.55 plane jets. The previous linear stability analyses showed that the phase velocity of most unstable 3D A1 mode was less than the ambient speed of sound. The result of 2D DNS shows that the amplification of a 2D A1 mode generates strong Mach waves. 3D DNS with A1 oblique modes indicates that the growth of A1 oblique modes have a crucial effect of 3D flow developments and that a less amplification of the 2D A1 mode yields weak Mach waves. These results suggest that quick decreases of the jet centerline velocity caused by the growth of 3D A1 mode restrain the strong Mach wave emission.
DNSによる超音速自由せん断流における音波放出機構の研究
nalsp0057049.pdf
(660.79KB)
