書誌事項
- タイトル別名
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- Effect of Inflow Boundary Layer Thickness on Scramjet Inlet Flowfields.
- スクラム ジェット インレットナイ ニ オケル キョウカイソウ リュウニュウ
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Flowfields about a scramjet inlet model were numerically simulated by the Thin-Layer Navier-Stokes equations, and effect of inflow boundary layer thickness was investigated. The computations were conducted for inflow Mach number of 3.4. Although pressure at the throat region is relatively constant for various boundary layer thickness, corresponding flow pattern near the top wall was very different to each other, and the total pressure recovery decreased with the boundary layer thickness. The spilled impulse function increased with the thickness of inflow boundary layer, and stream thrust function of the spilled air slightly increased with the boundary layer thickness. The tendency was due to the increase of the separating region with the boundary layer thickness.
収録刊行物
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- 日本航空宇宙学会誌
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日本航空宇宙学会誌 45 (519), 216-221, 1997
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390282679454245376
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- NII論文ID
- 10002861478
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- NII書誌ID
- AN00189072
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- ISSN
- 24241369
- 00214663
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- NDL書誌ID
- 4184048
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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
- NDL
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- 抄録ライセンスフラグ
- 使用不可