空間発展DNSによるM=3超音速境界層の遷移機構の研究
書誌事項
- タイトル別名
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- Study of transition mechanism in a supersonic boundary layer at M = 3 using spatial DNS
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説明
Spatial direct numerical simulations are used to study the formation and development of three-dimensional structures in a supersonic flat plate boundary layer, where the free-stream Mach number is three and the Reynolds number at the inlet based on the displacement thickness 1,000. Random disturbances are superimposed on the laminar profile at the inlet plane of the boundary layer computational box. Hairpin vortices are generated in an intermittent manner on a low speed streak downstream after the low/high speed streaks formation. The numerical turbulent velocity fluctuations are in good agreement with the experimental data of the supersonic turbulent boundary layer for M = 2.9.
資料番号: AA0049208016
レポート番号: JAXA-SP-05-012
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35回・第36回 = JAXA Special Publication: Proceedings of the 35th and 36th 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35回・第36回 = JAXA Special Publication: Proceedings of the 35th and 36th JAXA Workshops on Investigation and Control of Boundary-Layer Transition JAXA-SP-05-012 51-52, 2006-02-01
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
- 1050574036239172992
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- NII論文ID
- 120006829464
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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/1696/00006192/
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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
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