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慣性飛行時の軸対象物体の流体解析
https://jaxa.repo.nii.ac.jp/records/6149
https://jaxa.repo.nii.ac.jp/records/61498f83e4f8-2360-465f-8645-7e0be45b22bf
名前 / ファイル | ライセンス | アクション |
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49212016.pdf (711.0 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 | 慣性飛行時の軸対象物体の流体解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 自由飛行 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 軸対称物体 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 細長い物体 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 揚力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 抗力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 迎角 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 時間発展 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 陰的近似因子化法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 速度ベクトル | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | free flight | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | axisymmetric body | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | slender body | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lift | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | drag | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | angle of attack | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | time evolution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | implicit approximate factorization method | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | velocity vector | |||||
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 | Study of numerical simulation of flow over an axisymmetric body in free flight | |||||
著者 |
西川, 進栄
× 西川, 進栄× 海田, 一哉× Sun, J.× 石出, 忠輝× Nishikawa, Nobuhide× Kaita, Kazuya× Sun, J.× Ishide, Tadateru |
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著者所属 | ||||||
千葉大学 工学部 | ||||||
著者所属 | ||||||
千葉大学 大学院 | ||||||
著者所属 | ||||||
千葉大学 大学院 | ||||||
著者所属 | ||||||
木更津工業高等専門学校 | ||||||
著者所属(英) | ||||||
en | ||||||
Chiba University Faculty of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Chiba University Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
Chiba University Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
Kisarazu National College of Technology | ||||||
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: 航空宇宙数値シミュレーション技術シンポジウム2005論文集 en : JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005 巻 JAXA-SP-05-017, p. 100-105, 発行日 2006-02-28 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Three-dimensional flow around the slender body, such as aircraft body or rocket cause drastic variation of flow with high angle of attack and have considerable influence on the aerodynamic characteristics. Here the projectile in the inertia flight after thrust of the body has been stopped is studied numerically by a finite difference scheme. This study aims at clarifying the mechanism of free flight, which is affected by the pitching and gravity on body. The initial condition is the flow at steady 'flight' which develops just after the power of engine is shutdown and the vehicle starts free flight with inertia. It has been predicted that in the lower Reynolds number less than 100,000 the flow is symmetric. Therefore, in this numerical study, the flow over a paraboloidal-nose cylinder at pitching rotation in 'free flight' is considered for Reynolds numbers lower than 100,000. The coordinate system fixed on the body, which yields additional terms in Navier Stokes equation. The dual-time pseudo compressibility code is applied for incompressible case, instead PC-TVD scheme for Mach = 0.3 case. The Newton's 2nd law is used with the balance of aerodynamic force and gravity together with angular momentum equation. The aerodynamic coefficients Cd, Cl, Cm are discussed, as well as the trajectory of body. | |||||
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: AA0049212016 | |||||
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-05-017 |