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超音速/極超音速飛翔体周りの流れ場の新しい計算手法
https://fukuyama-u.repo.nii.ac.jp/records/8156
https://fukuyama-u.repo.nii.ac.jp/records/8156871fb976-bdf8-46fd-a213-df69c05c937e
名前 / ファイル | ライセンス | アクション |
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Item type | 紀要論文(ELS) / Departmental Bulletin Paper(1) | |||||
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公開日 | 2003-12-01 | |||||
タイトル | ||||||
タイトル | 超音速/極超音速飛翔体周りの流れ場の新しい計算手法 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | A New Calculation Method of Flowfield around Supersonic/Hypersonic Vehicles | |||||
言語 | ||||||
言語 | jpn | |||||
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 | 極超音速流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 再突入カプセル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 有限要素法 | |||||
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 | Hypersonic Flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Re-entry capsule | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Finite Element Method | |||||
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 | departmental bulletin paper | |||||
ページ属性 | ||||||
内容記述タイプ | Other | |||||
内容記述 | P(論文) | |||||
著者名(日) |
中村, 弘明
× 中村, 弘明× 真鍋, 圭司× 瀬崎, 新士× 西尾, 正富 |
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著者名よみ | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43791 | |||||
姓名 | ナカムラ, ヒロアキ | |||||
著者名よみ | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43792 | |||||
姓名 | マナベ, ケイジ | |||||
著者名よみ | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43793 | |||||
姓名 | セザキ, シンジ | |||||
著者名よみ | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43794 | |||||
姓名 | ニシオ, マサトミ | |||||
著者名(英) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43795 | |||||
姓名 | NAKAMURA, Hiroaki | |||||
言語 | en | |||||
著者名(英) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43796 | |||||
姓名 | MANABE, Keiji | |||||
言語 | en | |||||
著者名(英) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43797 | |||||
姓名 | SEZAKI, Shinji | |||||
言語 | en | |||||
著者名(英) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 43798 | |||||
姓名 | NISHIO, Masatomi | |||||
言語 | en | |||||
著者所属(日) | ||||||
値 | 福山大学工学部工学部機械工学科 | |||||
著者所属(日) | ||||||
値 | 福山大学工学部工学部機械工学科 | |||||
著者所属(日) | ||||||
値 | 福山大学工学部工学部機械工学科 | |||||
著者所属(日) | ||||||
値 | 福山大学工学部工学部機械工学科 | |||||
著者所属(英) | ||||||
言語 | en | |||||
値 | Department of Mechanical Engineering, Faculty of Engineering, Fukuyama University | |||||
著者所属(英) | ||||||
言語 | en | |||||
値 | Department of Mechanical Engineering, Faculty of Engineering, Fukuyama University | |||||
著者所属(英) | ||||||
言語 | en | |||||
値 | Department of Mechanical Engineering, Faculty of Engineering, Fukuyama University | |||||
著者所属(英) | ||||||
言語 | en | |||||
値 | Department of Mechanical Engineering, Faculty of Engineering, Fukuyama University | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A calculation method of flowfield around supersonic/hypersonic vehicles based on the finite element method (FEM) has been presented. In this study, the pressure term of Navier-Stokes equations was included in the flux vector. By performing this scheme, the pressure term could be expressed as a non-differential form in the weighted residual equations. This idea made it possible to calculate compressible flowfields including a shock wave with dramatic less error and better stability with a very small artificial viscosity, compared to conventional FEM calculations. The correctness of the present method was confirmed by comparing shock shapes obtained by the Schlieren system and by comparing streamlines obtained by the electric discharge method. The comparisons were carried out by investigating the flowfield around a Mach 10 MESUR capsule. | |||||
雑誌書誌ID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00217655 | |||||
書誌情報 |
福山大学工学部紀要 巻 27, p. 259-266, 発行日 2003-12 |