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超音速複葉翼の干渉流れに関する実験的研究
https://jaxa.repo.nii.ac.jp/records/5610
https://jaxa.repo.nii.ac.jp/records/56103ec26a0b-48bf-44bf-b3bf-b86f051563df
名前 / ファイル | ライセンス | アクション |
---|---|---|
63742004.pdf (1.0 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 超音速複葉翼の干渉流れに関する実験的研究 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ブーゼマンエアフォイル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 複葉機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 旅客機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 衝撃波干渉 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧縮波 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 壁面圧 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力測定 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 感圧塗料 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速風洞 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞模型 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Busemann airfoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | biplane | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | passenger aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shock wave interaction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | compression wave | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wall pressure | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure measurement | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure sensitive paint | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic wind tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel model | |||||
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 | Experimental study on interference flow of a supersonic Busemann biplane | |||||
著者 |
永井, 大樹
× 永井, 大樹× 齋藤, 賢一× 小川, 俊広× 浅井, 圭介× Nagai, Hiroki× Saito, Kenichi× Ogawa, Toshihiro× Asai, Keisuke |
|||||
著者所属 | ||||||
東北大学 大学院工学研究科 | ||||||
著者所属 | ||||||
東北大学 大学院工学研究科 | ||||||
著者所属 | ||||||
東北大学流体科学研究所 | ||||||
著者所属 | ||||||
東北大学 大学院工学研究科 | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University Graduate School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University Graduate School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Fluid Science, Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University Graduate School of Engineering | ||||||
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39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2007論文集 en : JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007 巻 JAXA-SP-07-016, p. 22-27, 発行日 2008-02-29 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An interest in Busemann biplane has been revived and the feasibility of the supersonic biplane is now under investigation by many researchers. However, these studies are based mainly on CFD (Computational Fluid Dynamics) calculations and not validated by experiment so that a discussion on the wave cancellation mechanism between the two wings is very limited. The objective of this research is to measure the wing surface pressure distribution on a Busemann biplane and to study the two-dimensional interference phenomenon between the two wings. Since the Busemann biplane wings are so thin (the wing thickness ratio is 0.05) that it is difficult to install static pressure taps on the model. In this experiment, we used Pressure-Sensitive Paint (PSP) to measure surface pressure distributions on the model. PSP is an optical pressure measurement technique based on photochemical reaction called 'oxygen quenching'. This is a coating type sensor and considered only means to measure pressure fields on a thin airfoil model. In this study, wind tunnel experiment was conducted in a 60 mm x 60 mm indraft supersonic wind tunnel. The surface pressure distribution obtained using PSP were compared with CFD results and the Schlieren images. The complicated three-dimensional interference phenomenon between the two wings, including shock wave/boundary layer interactions was analyzed. On the basis of these experimental results, the wave cancellation mechanism of the Busemann biplane is discussed. | |||||
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: AA0063742004 | |||||
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-07-016 |