ロケットエンジンノズル形状と横力の発生について
書誌事項
- タイトル別名
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- Influence of a shape of rocket engine nozzle on side-load characteristics during start-up transient
この論文をさがす
説明
Axisymmetric computation was applied to the transient flow in a sub-scaled LE-7A nozzle with three different configurations of a joint section between its upper nozzle and nozzle extension sections, such as a backward facing step for film-cooling, to investigate the influences of the flow disturbances produced by such nozzle surface shapes on the transient flow characteristics and to examine the possible cause of side-loads observed in the experiments. Rapid movement of the separation point occurred when it passed through the joint section. One of reasons for the occurrence of a highly asymmetrical flow causing large side-load is considered to be that the location of the separation point becomes very sensitive to the flow condition when the separation point passes through the joint section.
資料番号: AA0045948029
レポート番号: NAL SP-57
収録刊行物
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- 航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2002論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002
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航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2002論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002 57 160-165, 2003-03
航空宇宙技術研究所
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キーワード
- ロケットエンジンノズル
- 横力特性
- 軸対称計算
- 過渡流
- 計算グリッド
- CFD
- 剥離流
- 燃焼室
- 温度分布
- 研究開発
- 圧力勾配
- ノズル圧比
- Navier-Stokes方程式
- rocket engine nozzle
- side-load characteristic
- axisymmetric computation
- transient flow
- computational grid
- separated flow
- combustion chamber
- temperature distribution
- research and development
- pressure gradient
- nozzle pressure ratio
- Navier-Stokes equation
詳細情報 詳細情報について
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- CRID
- 1050292561232749056
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- NII論文ID
- 120006838954
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- NII書誌ID
- AN10097345
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- ISSN
- 0289260X
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- Web Site
- http://id.nii.ac.jp/1696/00038244/
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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
