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Visualization of Unsteady Behavior of Shock Waves around Supersonic Intake installed in Shock Tunnel
https://jaxa.repo.nii.ac.jp/records/4135
https://jaxa.repo.nii.ac.jp/records/41355b039c2b-c72e-40a6-aa12-4c4f5e82e257
名前 / ファイル | ライセンス | アクション |
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62070027.pdf (302.2 kB)
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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 | ||||||
言語 | en | |||||
タイトル | Visualization of Unsteady Behavior of Shock Waves around Supersonic Intake installed in Shock Tunnel | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic intake | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | buzz | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shock tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow visualization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure-sensitive paint | |||||
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 | |||||
著者 |
田中, 成明
× 田中, 成明× 水書, 稔治× Tanaka, Naruaki× Mizukaki, Toshiharu |
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著者所属 | ||||||
東海大学大学院工学研究科航空宇宙学専攻 | ||||||
著者所属 | ||||||
東海大学大学院工学研究科航空宇宙学専攻 | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Aeronautics and Astronautics, Graduate School, Tokai University | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Aeronautics and Astronautics, Graduate School, Tokai University | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構(JAXA) | |||||
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 en : JAXA Special Publication 巻 JAXA-SP-13-001E, p. 327-334, 発行日 2013-11-30 |
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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 | 5th Symposium on Integrating CFD and Experiments in Aerodynamics (October 3-5, 2012, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | This paper describes unsteady behavior of shock waves around supersonic intake at Mach 2.5. The experiment carried out by small shock tunnel. Flow visualization was conducted with shadowgraph method and pressure-sensitive paint (PSP). A fast response anodized aluminum pressure-sensitive paint (AA-PSP) was used in the experiment. And to confirm the valid of experimental results, numerical calculation were performed by compressible Navier-Stokes equations with Weighted Average Flux (WAF) method and Adaptive Mesh Refinement (AMR). From the results of shock wave structures and pressure distribution, we confirmed shock waves behavior around the supersonic intake model at subcritical state. It considers occurring buzz. | |||||
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: AA0062070027 | |||||
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-13-001E |