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飛行実験における遷移解析
https://jaxa.repo.nii.ac.jp/records/5443
https://jaxa.repo.nii.ac.jp/records/544336a34384-8323-4c00-beec-cd6538ae68f2
名前 / ファイル | ライセンス | アクション |
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64239007.pdf (8.4 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 | 飛行実験における遷移解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Natural Laminar Flow, Boundary Layers, Transition Measurement, Transition Prediction, 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 | Transition analysis for the flight test of supersonic experimental airplane (NEXST-1) | |||||
著者 |
徳川, 直子
× 徳川, 直子× 郭, 東潤× 吉田, 憲司× 上田, 良稲× 石川, 敬掲× Tokugawa, Naoko× Kwak, Dong-Youn× Yoshida, Kenji× Ueda, Yoshine× Ishikawa, Hirotaka |
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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 | ||||||
東京ビジネスサービス | ||||||
著者所属 | ||||||
三向ソフトウェア開発 | ||||||
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 | ||||||
Tokyo Business Service | ||||||
著者所属(英) | ||||||
en | ||||||
Sanko Soft | ||||||
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 | Transition location of an unmanned and scaled supersonic experimental airplane (NEXST-1) is measured by the flight test. The wing of NEXST-1 is designed with our original CFD-based inverse design method to apply the natural laminar flow concept. It is the first challenge to apply the natural laminar flow wing concept to a supersonic vehicle. The concept is tried to validate by measuring the surface pressure and the transition location. In this paper, the flight data analysis to detect transition location by four kinds of sensors and the results are summarized. Also the development of numerical transition prediction and its results are summarized. The transition location at the design condition, which is detected experimentally, delays in contrast with that at the off-design point. Therefore the natural laminar flow effect is confirmed. | |||||
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: AA0064239007 | |||||
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 |