Hiroshima University Graduate School of Engineering
Hiroshima University Graduate School of Engineering
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集 第37回・第38回
雑誌名(英)
JAXA Special Publication: Proceedings of the 37th and 38th JAXA Workshops on Investigation and Control of Boundary-Layer Transition
巻
JAXA-SP-06-013
ページ
47 - 48
発行年
2007-02-23
抄録（英）
A study of compressible subsonic/supersonic transitional and turbulent flow in a plane channel with isothermal walls has been performed using a spatially developing DNS (Direct Numerical Simulation). Random disturbance is artificially introduced at the inlet of the computational channel, which yields streamwise vortices and low/high speed streaks downstream. At high Mach number flows, the isothermal boundary conditions give rise to a flow that is strongly influenced by wall-normal gradients of mean density and temperature. These gradients are found to cause major differences of the transitional streak structure between subsonic and supersonic channel flows.
圧縮性平面チャネル流の乱流遷移構造
63156014.pdf
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