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溝付き平板上の極超音速流れに関する研究
https://jaxa.repo.nii.ac.jp/records/4732
https://jaxa.repo.nii.ac.jp/records/4732ca051c13-67b9-4bf5-9e4c-d6d89457a039
名前 / ファイル | ライセンス | アクション |
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64967025.pdf (1.8 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 溝付き平板上の極超音速流れに関する研究 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | A Study on hypersonic flow over a flat plate with narrow channels | |||||
著者 |
大道, 勇哉
× 大道, 勇哉× 鈴木, 宏二郎× Omichi, Yuya× Suzuki, Kojiro |
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著者所属 | ||||||
東京大学大学院新領域創成科学研究科基盤科学研究系先端エネルギー工学専攻 | ||||||
著者所属 | ||||||
東京大学大学院新領域創成科学研究科基盤科学研究系先端エネルギー工学専攻 | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Advanced Energy, Graduate School of Frontier Science, University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Advanced Energy, Graduate School of Frontier Science, University of Tokyo | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集 en : JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 巻 JAXA-SP-10-012, 発行日 2011-02-28 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP) | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25, 2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | At the development of hypersonic vehicles, it is quite important to estimate the aerodynamic heating with high accuracy, because hypersonic vehicles are exposed to high temperature and/or high pressure flow behind a strong shock wave formed over the body. A hypersonic vehicle often has small irregularities on its body surface. For example, the gaps between the tiles for the thermal protection may work as the surface roughness. Such irregularity on the body surface causes local peaks of aerodynamic heating. In addition, it may enhance laminar-turbulent transition in the boundary layer flow. In this study, we numerically analyze the effect of the surface roughness by the presence of narrow channels opening flush with a flat plate in a hypersonic flow at Mach number 7. To represent the tile gap over a hypersonic vehicle, the H-form channel layout composed of one longitudinal and two lateral channels is considered. The numerical simulation has been conducted by solving the three-dimensional laminar Navier-Stokes equations with SLAU scheme. The results show that a shock wave appears and the aerodynamic heating is significantly augmented near the downstream edge of channels. Such heating augmentation strongly depends on geometric and flow parameters, such as, the width of channels or angle of attack. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0064967025 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-10-012 |