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Wing flutter computation using spectral volume method for hybrid unstructured mesh
https://jaxa.repo.nii.ac.jp/records/3409
https://jaxa.repo.nii.ac.jp/records/340985b47be4-76ae-4338-bd19-e2e5897839a0
名前 / ファイル | ライセンス | アクション |
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AA1630046016.pdf (3.2 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2017-04-27 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Wing flutter computation using spectral volume method for hybrid unstructured mesh | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Unstructured Mesh | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Fluid-Structure Interaction | |||||
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 |
澤木, 悠太
× 澤木, 悠太× 舘岡, 誠也× 澤田, 恵介× Sawaki, Yuta× Tateoka, Seiya× Sawada, Keisuke |
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著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
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(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: Proceedings of the First International Symposium on Flutter and its Application 巻 JAXA-SP-16-008E, p. 157-168, 発行日 2017-03-15 |
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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 | First International Symposium on Flutter and its Application (May 15-17, 2016. Mielparque-tokyo), Minato-ku, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Toward accurate prediction of transonic wing flutter phenomenon, an implicit spectral volume method is extended to employ the ALE formulation for moving and deforming grid, and unstructured hybrid meshes for higher computational efficiency. The developed aeroelastic analysis code is applied to compute the transonic flutter of the AGARD 445.6 wing and a rectangular unswept wing. In this study, modal structure analysis is employed. The eigen frequencies and mode shapes of each mode in a reference are employed for the AGARD 445.6 wing flutter analysis. For the rectangular wing flutter analysis, we make the structure plate model using NASTRAN. It is shown that the computed flutter speed index and flutter frequency agree well with the experimental data at subsonic freestream condition, and considering viscous effects improve the computed results in supersonic freestream regime for the AGARD 445.6 wing. In the rectangular flutter case, the flutter speed index at transonic dip cannot be obtained quantitatively. Accounting for viscous effects slightly improve the flutter speed index. On the other hand, the flutter frequency is significantly improved by solving RANS equations at the transonic dip condition compared with that obtained by Euler computation. The cause for this improvement is under consideration. | |||||
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: AA1630046016 | |||||
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-16-008E |