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非保存形のFEM定式による衝撃波解析
https://jaxa.repo.nii.ac.jp/records/4916
https://jaxa.repo.nii.ac.jp/records/4916243c51a2-7f73-4ba4-a2af-4c701ce00cef
名前 / ファイル | ライセンス | アクション |
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64672018.pdf (532.2 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 | 非保存形のFEM定式による衝撃波解析 | |||||
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 | Shock Wave Analysis by Non-conservative FEM Formulation | |||||
著者 |
真鍋, 圭司
× 真鍋, 圭司× 西尾, 正富× Manabe, Keiji× Nishio, Masatomi |
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著者所属 | ||||||
福山大学工学部機械システム工学科 | ||||||
著者所属 | ||||||
福山大学工学部機械システム工学科 | ||||||
著者所属(英) | ||||||
en | ||||||
Faculty of Engineering, Fukuyama University | ||||||
著者所属(英) | ||||||
en | ||||||
Faculty of Engineering, Fukuyama 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: 第41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2009論文集 en : JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009 巻 JAXA-SP-09-011, 発行日 2010-02-26 |
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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 | 平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター | |||||
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 | 18 June-19 June, 2009, Japan Aerospace Exploration Agency | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The hypersonic -flow including shock wave problems are usually analyzed by solving compressible flow equations written by conservative form. In this study, shock wave analysis is carried out by solving non-conservative form of governing equations by Finite Element Method (FEM). First, it is shown that the non-conservative form of 1-dimensional Burgers equation can be properly solved by using upwind scheme of Finite difference method (FDM). This FDM formulation for 1-dimensional non-conservative Burgers equation can be obtained from FEM by using 1-dimensional linear shape function and Upwind Petrov-Galerkin (SUPG) method. Consequently the same computational results of FDM and FEM for 1-dimensional Burgers equation is obtained. Second, compressible Navier-Stokes equations are changed to the non-conservative form. It is important for analyzing shock wave to consider artificial viscosity term, therefore, the non-conservative formulation is conducted for the equation including artificial viscosity term. The detail of the non-conservative formulations of governing equations are shown. This type of equations are introduced to the program of FEM, and the 2-dimensional axisymmetric problem is calculated. The calculation result of shock wave around the Re-entry capsule under the condition of Mach 10 are shown, and the good agreement with experimental result is obtained. It is concluded that non-conservative form of governing equations of compressible fluid can also analyze the shock wave by considering the artificial viscosity term. | |||||
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: AA0064672018 | |||||
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-09-011 |