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複葉超音速翼空力設計の現状と課題
https://jaxa.repo.nii.ac.jp/records/5963
https://jaxa.repo.nii.ac.jp/records/5963e9b3ef49-7a93-402a-b8e4-6f0f7967f4f2
名前 / ファイル | ライセンス | アクション |
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63154019.pdf (1.4 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 | 複葉超音速翼空力設計の現状と課題 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | Busemann複葉機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速複葉機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | チョーク流れ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 衝撃波 | |||||
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 | 超音速輸送機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 抗力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | インテークディフューザ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 不始動条件 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic airfoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Busemann biplane | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic biplane | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | choked flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | shock wave | |||||
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 | supersonic transport | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | drag | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | intake diffuser | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | unstart condition | |||||
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 | Aerodynamic design of supersonic biplane: Current status and future direction | |||||
著者 |
米澤, 誠仁
× 米澤, 誠仁× 山下, 博× 大林, 茂× 楠瀬, 一洋× Yonezawa, Masahito× Yamashita, Hiroshi× Obayashi, Shigeru× Kusunose, Kazuhiro |
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著者所属 | ||||||
東北大学流体科学研究所 | ||||||
著者所属 | ||||||
東北大学流体科学研究所 | ||||||
著者所属 | ||||||
東北大学流体科学研究所 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Fluid Science, Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Fluid Science, Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Fluid Science, Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
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: 航空宇宙数値シミュレーション技術シンポジウム2006論文集 en : JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006 巻 JAXA-SP-06-010, p. 101-106, 発行日 2006-12-01 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Nowadays, the development of Supersonic Transport (SST) is attracting international attention again. However, in supersonic flights, we face the problem of 'sonic boom', which is induced by a shock wave. To alleviate the problem of sonic boom, the idea of reducing shock wave using Busemann biplane has been proposed. The interaction of shock waves between the two wings cancels out or reduces the shock waves created by individual wings. This research discusses two issues about Busemann biplane. One is the unstarted condition during acceleration. The other is the three-dimensional configuration of Busemann biplane. Unstarted condition happens due to the unsatisfied condition with Kantrowitz Donaldson Criteria. Unstarted condition that holds in the criteria is confirmed by analyzing accelerate phenomenon using Computational Fluid Dynamics (CFD) analysis. The other important issue is that the shock front should be planar to cancel out the shock waves between two wings. The caret wing induces a planar shock front. Three caret wing configurations are analyzed to examine how the planar shock front are created using CFD analysis. | |||||
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: AA0063154019 | |||||
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-06-010 |