圧縮性平面チャネル流の乱流遷移構造
書誌事項
- タイトル別名
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- Transition to turbulence of compressible plane channel flow
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説明
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.
資料番号: AA0063156014
レポート番号: JAXA-SP-06-013
収録刊行物
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- 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 = JAXA Special Publication: Proceedings of the 37th and 38th JAXA Workshops on Investigation and Control of Boundary-Layer Transition
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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 = JAXA Special Publication: Proceedings of the 37th and 38th JAXA Workshops on Investigation and Control of Boundary-Layer Transition JAXA-SP-06-013 47-48, 2007-02-23
宇宙航空研究開発機構
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詳細情報 詳細情報について
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- CRID
- 1050574036224813184
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- NII論文ID
- 120006829338
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- NII書誌ID
- AA11984031
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- ISSN
- 1349113X
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- Web Site
- http://id.nii.ac.jp/1696/00005927/
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- 本文言語コード
- ja
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- 資料種別
- conference paper
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- データソース種別
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- IRDB
- CiNii Articles
