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FR 法による高次精度非構造オーバーセット格子法の構築
https://jaxa.repo.nii.ac.jp/records/2950
https://jaxa.repo.nii.ac.jp/records/2950dff83c58-2090-4389-ac70-3cadb2c5988a
名前 / ファイル | ライセンス | アクション |
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AA1830029021.pdf (7.1 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2019-02-28 | |||||
タイトル | ||||||
タイトル | FR 法による高次精度非構造オーバーセット格子法の構築 | |||||
言語 | ||||||
言語 | jpn | |||||
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 | Development of a high-order unstructured overset-grid method based on flux-reconstruction scheme | |||||
著者 |
芳賀, 臣紀
× 芳賀, 臣紀× 嶋, 英志× Haga, Takanori× Shima, Eiji |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
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: 第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム論文集 en : JAXA Special Publication: Proceedings of the 50th Fluid Dynamics Conference / the 36th Aerospace Numerical Simulation Symposium 巻 JAXA-SP-18-005, p. 177-182, 発行日 2019-02-25 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎 | |||||
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 | 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The high-order flux reconstruction (FR) method is extended for overset-grid capability aiming for further geometrical flexibility and multiple moving body problems. Compact data dependency of the FR method facilitates inter-grid data communication without using interpolation stencils. The developed overset FR method is applied to solve benchmark problems including 2D inviscid vortex propagation and acoustic scattering around a cylinder. The results are compared with the analytical solutions in order to verify the accuracy of the proposed method. The developed overset FR solver is applied to Large-eddy simulation of supersonic three-nozzle clustered jet and its interaction with the launch pad. By using the overset grids, it is possible to perform analysis by changing the lift amount, the nozzle configuration (3-clustered or single), and the shape of the launch pad without changing the all computational grids. | |||||
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 | |||||
ISSNONLINE | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 2433-2232 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA1830029021 | |||||
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-18-005 |