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Numerical Analysis of the ONERA-M6 Wing with Wind Tunnel Wall Interference
https://jaxa.repo.nii.ac.jp/records/22618
https://jaxa.repo.nii.ac.jp/records/22618c50a197a-0ffe-4568-bed2-7024e60b7690
Item type | 学術雑誌論文 / Journal Article(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-08-12 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Numerical Analysis of the ONERA-M6 Wing with Wind Tunnel Wall Interference | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Wall Interference, Porous Wall | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Porous Wall | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ONERA-M6 Wing | |||||
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_6501 | |||||
資源タイプ | journal article | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
著者 |
南部, 太介
× 南部, 太介× 橋本, 敦× 青山, 剛史× 佐藤, 哲也× Nambu, Taisuke× Hashimoto, Atsushi× Aoyama, Takashi× Sato, Tetsuya |
|||||
著者所属 | ||||||
早稲田大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構研究開発本部(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構研究開発本部(JAXA) | ||||||
著者所属 | ||||||
早稲田大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Waseda University | ||||||
著者所属(英) | ||||||
en | ||||||
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Waseda University | ||||||
出版者 | ||||||
出版者 | 日本航空宇宙学会 | |||||
出版者(英) | ||||||
出版者 | The Japan Society for Aeronautical and Space Sciences | |||||
書誌情報 |
en : Transactions of the Japan Society for Aeronautical and Space Sciences 巻 58, 号 1, p. 7-14, 発行日 2015-01-04 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The flow around an ONERA-M6 wing, including the effect of wind tunnel wall interference, is computed using CFD analysis with a porous wall model. The computational domain sets porous walls at the top and bottom of the wing section similar to actual wind tunnel experiments. The computational result captures almost the same shock wave shape as the wind tunnel. This could not be computed exactly in previous works that did not include wall effects. The interference of the porous walls reduces the Mach number and attack angle of the flow, and these effects alter the swept angle of front shock wave and the location of rear shock wave. The aerodynamics coefficients are also affected by the wall interference. The lift coefficient becomes smaller due to the reduction in attack angle. The lower Mach number decreases the drag coefficient, while the reduction in attack angle causes additional drag by a mechanism similar to induced drag. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: 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 illustrations | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0549-3811 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA0086707X | |||||
DOI | ||||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.2322/tjsass.58.7 | |||||
関連名称 | info:doi/10.2322/tjsass.58.7 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1520033000 |