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圧縮揚力による超音速デルタ翼の揚抗比増加に関する数値解析
https://jaxa.repo.nii.ac.jp/records/5609
https://jaxa.repo.nii.ac.jp/records/560952fb1218-ac05-4ee7-b3cf-0edbd163b688
名前 / ファイル | ライセンス | アクション |
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63742003.pdf (503.0 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 | ||||||
タイトル | 圧縮揚力による超音速デルタ翼の揚抗比増加に関する数値解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧縮揚力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 揚抗比 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | デルタ翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 前縁 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 剥離流 | |||||
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 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力係数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 航空機設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算流体力学 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | compression lift | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lift drag ratio | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | delta wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | leading edge | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | separated flow | |||||
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 | aerodynamic characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic coefficient | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aircraft design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
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 | Numerical analysis on L/D augmentation of supersonic delta wing by using compression lift | |||||
著者 |
金森, 正史
× 金森, 正史× 今村, 宰× 鈴木, 宏二郎× Kanamori, Masashi× Imamura, Osamu× Suzuki, Kojiro |
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著者所属 | ||||||
東京大学 大学院 | ||||||
著者所属 | ||||||
東京大学 大学院新領域創成科学研究科 | ||||||
著者所属 | ||||||
東京大学 大学院新領域創成科学研究科 | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School of Frontier Sciences | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School of Frontier Sciences | ||||||
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. 17-21, 発行日 2008-02-29 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | We numerically analyze supersonic flows around a delta wing with bent wing tip. The results show that the lift and drag forces decrease with the increase in the bending angle. But the local augmentation is observed around the hinge line of bending in the spanwise distribution. On the other hand, the lift-to-drag ratio keeps almost the same value independent of the bending angle. This phenomenon is significantly related to the interaction between shock waves generated at the wing root and tip. The mechanism of lift augmentation is explained as the 'compression lift' effect due to this shock-shock interaction. | |||||
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: AA0063742003 | |||||
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 |