書誌事項
- タイトル別名
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- Shock-Induced Turbulent Boundary Layer Separation in Supersonic Nozzles.
- チョウ オンソク ノズル ナイ ノ ショウゲキハ ニヨル ランリュウ キョウカイ ソウ ノ ハクリ
- チョウオンソク ノズルナイ ノ ショウゲキハ ニヨル ランリュウ キョウカイソ
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Experiments on the shock wave/turbulent boundary layer interaction were conducted at the free stream Mach number M1e of 1.97 to 2.50 and the Reynolds number based on the boundary layer thickness Reδ1 of 3.1×104 to 5.8×104 using a supersonic nozzle having a divergent half angle of 10 degrees. Nozzle wall static pressure measurements and the schlieren optical observation of the interaction region were carried out. Also, the effects of M1e and Reδ1 on the shock-induced turbulent boundary layer separation were investigated theoretically. As a result, the analytical results of the ratio ps/p1 of the separation pressure ps to the pressure at the onset of the interaction p1 were found to increase with increasing M1e for a fixed Reδ1 and to increase with increasing Reδ1 for a fixed M1e and to provide excellent agreement with the experimental results on the shock-induced turbulent boundary layer separation.
収録刊行物
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- 日本機械学会論文集Ｂ編
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日本機械学会論文集Ｂ編 63 (607), 879-886, 1997
一般社団法人 日本機械学会
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詳細情報 詳細情報について
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- CRID
- 1390001205894019456
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- NII論文ID
- 120004225403
- 130004222531
- 110002396261
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- NII書誌ID
- AN00187441
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- ISSN
- 18848346
- 03875016
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- HANDLE
- 10232/14431
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- NDL書誌ID
- 4171239
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- IRDB
- NDL
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可