WEKO3
アイテム
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極超音速流れにおける軸対称物体回りのフィルムクーリング冷却法に関する研究
https://jaxa.repo.nii.ac.jp/records/37858
https://jaxa.repo.nii.ac.jp/records/3785810370019-bf1d-4932-a3b3-0f7e0aa2385e
名前 / ファイル | ライセンス | アクション |
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nalsp0027021.pdf (518.2 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 極超音速流れにおける軸対称物体回りのフィルムクーリング冷却法に関する研究 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | フィルム冷却 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 再突入物体冷却 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力加熱 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 極超音速飛翔体 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱防御 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 極超音速境界層 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 表面熱流束 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 表面吹出し冷却 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流れ数値シミュレーション | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD応用 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD対風洞相関 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙往還機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 再突入物体 | |||||
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 | ナビエ・ストークス方程式 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | film cooling | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reentry body cooling | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic heating | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic flight vehicle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermal protection | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic boundary layer | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | surface heat flux | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | tangential blowing cooling | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical flow simulation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD application | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD wind tunnel correlation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reentry vehicle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reentry 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 | Navier Stokes equation | |||||
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 | Numerical simulation of film cooling effect around axisymmetric body in hypersonic flow field | |||||
著者 |
黒滝, 卓司
× 黒滝, 卓司× 中村, 淑子× 黒崎, 隆二郎× 片山, 雅之× 麻生, 茂× Kurotaki, Takuji× Nakamura, Yoshiko× Kurosaki, Ryujiro× Katayama, Masayuki× Aso, Shigeru |
|||||
著者所属 | ||||||
三菱電機 鎌倉製作所 | ||||||
著者所属 | ||||||
三菱電機 鎌倉製作所 | ||||||
著者所属 | ||||||
三菱電機 鎌倉製作所 | ||||||
著者所属 | ||||||
三菱電機 鎌倉製作所 | ||||||
著者所属 | ||||||
九州大学 工学部 航空工学科 | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Electric Corporation Kamakura Works | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Electric Corporation Kamakura Works | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Electric Corporation Kamakura Works | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Electric Corporation Kamakura Works | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu University Department of Aeronautics and Astronautics, Faculty of Engineering | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所特別資料 en : Special Publication of National Aerospace Laboratory 巻 27, p. 165-170, 発行日 1994-12 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 極超音速流中の軸対称物体における吹出しによるフィルム冷却効果を数値的に調べ、その結果を実験データと比較した。実験は在来型の衝撃風洞を用いて行った。主流マッハ数4.25で、半球状頭部模型の先端に設けたスロットから冷却用ガス(N2)を供給する。吹き出しは模型表面に接する向きで物体表面上の熱伝達を計測した。数値解析では、陰的有限差分解法を用いて軸対称完全ナビエ・ストークス方程式を解いた。時間積分にはLU-SGSを用い、対流項はRoeタイプの流束分割に基くMUSCL型のTVDスキームを用いた。数値解析結果は表面熱流束が著しく減ることを示し、これは実験でも同様で、数値解析と実験とは定性的に一致する。境界層内の流れを詳細に見ると2層から成り、内層は物体表面に沿う断熱壁の役割を果している。これらの特性は、この種の極超音速流におけるフィルム冷却効果の決定に本質的な関わりをもつと考えられる。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Film cooling effects due to mass addition on axisymmetric body in hypersonic flow field are numerically investigated and results of numerical simulation are compared with experimental data. Experiments are conducted by using a conventional shock tunnel. Free stream Mach number is 4.25 and cooling gas (N2) is supplied through the slot located at the nose of a hemisphere model. The direction of mass addition is tangential from the model surface and heat flux around the body is measured. In numerical analysis, axisymmetric full Navier-Stokes equations are solved by an implicit finite difference method. Lower Upper Symmetric Gauss Seidel (LU-SGS) scheme is used for the time integration and convective terms are evaluated by the MUSCL (Monotonic Upstream Schemes for Conservation Laws)-type Total Variation Diminishing (TVD) scheme based on Roe-type flux splitting. Numerical results show significant decreases of surface heat flux which are also obtained in experiments and agreement of numerical and experimental results are qualitatively good. More detailed investigation of the flow inside the boundary layer indicates that the boundary layer consists of two sublayers and that the inner layer plays a role of adiabatic wall structure on the surface. These characteristics are considered most essential in the determination of film cooling effects in this type of hypersonic flow. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0004174021 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL SP-27 |