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飛行実験におけるCFD解析
https://jaxa.repo.nii.ac.jp/records/5442
https://jaxa.repo.nii.ac.jp/records/544269f656fd-cb02-48bb-8838-8347f07dc6f8
名前 / ファイル | ライセンス | アクション |
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64239006.pdf (6.6 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 | 飛行実験におけるCFD解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SST, Computational Fluid Dynamics, Flight Testing | |||||
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 | CFD analysis on the flight test of supersonic experimental airplane (NEXST-1) | |||||
著者 |
石川, 敬掲
× 石川, 敬掲× 吉田, 憲司× 郭, 東潤× 川上, 浩樹× 徳川, 直子× Ishikawa, Hirotaka× Yoshida, Kenji× Kwak, Dong-Youn× Kawakami, Hiroki× Tokugawa, Naoko |
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著者所属 | ||||||
三向ソフトウェア開発 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属(英) | ||||||
en | ||||||
Sanko Soft | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
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: 小型超音速実験機(ロケット実験機)飛行実験データ解析完了報告 en : JAXA Special Publication 巻 JAXA-SP-08-008, 発行日 2009-02-27 |
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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 | 小型超音速実験機(ロケット実験機)飛行実験データ解析完了報告会(平成20年7月10日. 東京大学山上会館) | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Flight test on supersonic experimental airplane (NEXST-1) was conducted successfully by Japan Exploration Agency on October, 2005. A lot of aerodynamic data on the flight test were obtained. In this study those flight test data were compared with the numerical analysis to validate the design technologies. The effect of the additional parts, the aeroelastic deformation and boundary layer transition were taken into account in the CFD analysis for higher accuracy. Then this comparison highlighted the quantitative benefit of the natural laminar flow wing design concept. | |||||
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 | |||||
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: AA0064239006 | |||||
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-08-008 |