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κ-ε乱流モデルを用いた単翼素および多翼素型まわり非圧縮流れの有限要素法による解析
https://jaxa.repo.nii.ac.jp/records/39902
https://jaxa.repo.nii.ac.jp/records/39902f6f33046-62a6-4c9a-82e1-39762ddadd3c
名前 / ファイル | ライセンス | アクション |
---|---|---|
naltr01316.pdf (2.3 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | κ-ε乱流モデルを用いた単翼素および多翼素型まわり非圧縮流れの有限要素法による解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 乱流モデル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | カッパ・エプシロン乱流モデル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 単翼素 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 多翼素 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 非圧縮流れ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 有限要素法 | |||||
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 | ||||||
主題Scheme | Other | |||||
主題 | レイノルズ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | オイラースキーム | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 陰的オイラースキーム | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 迎角 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | フラップ偏角 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 翼まわり圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 揚力係数 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | turbulence model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | kappa epsilon turbulence model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | single component aerofoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | multicomponent aerofoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | incompressible flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | finite element method | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Navier Stokes equation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Reynolds number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Euler scheme | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | implicit Euler scheme | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | attack angle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flap angle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution around aerofoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lift coefficient | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Employment of kappa-epsilon turbulence model for finite-element analysis of flows over single- and multi-component aerofoils | |||||
著者 |
重見, 仁
× 重見, 仁× 伊藤, 婦美子× Shigemi, Masashi× Ito, Fumiko |
|||||
著者所属 | ||||||
航空宇宙技術研究所 新型航空機研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所 新型航空機研究グループ | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Advanced Aircraft Research Group | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Advanced Aircraft Research Group | ||||||
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報告 en : Technical Report of National Aerospace Laboratory 巻 1316, p. 1-19, 発行日 1996-12 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 非圧縮性ナビエ・ストークスの式を有限要素法によって解く計算コードに、高レイノルズ数型のκ-ε乱流モデルを組み合わせて、翼型まわりの流れを数値的に解くことを試みた。解くべき方程式は非線形性が強く、発散しやすい性質を持つが、陰的オイラースキームを用いて時間積分を実行し、さらに一様流中に潜在する乱れの存在を仮定した結果、安定な流れの解を得ることができた。迎角、フラップの偏角があまり大きくない場合の比較的おとなしい流れに対しては、計算で得られた翼型まわりの圧力分布、揚力は実験結果と良く一致し、この乱流モデルを用いる有効性が確認できた。しかし、流れが時間とともに振動する場合や、迎角の大きい場合には、実験値と計算値の一致の度合いは低くなった。陰的オイラースキームの採用に伴って必要となった大規模な1次方程式系の解法として、できる限り少ない計算メモリで高速に解の得られる直接解法コードを新たに開発して用いた。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Finite-element analysis code to solve incompressible Navier-Stokes equations was incorporated into the kappa-epsilon turbulence model of high Reynolds number type, and was applied to flows around single- and multicomponent aerofoils. Although the relevant equations are highly nonlinear and, therefore, their solutions are easy to diverge, the employment of the implicit Euler scheme for time marching integral and the introduction of background turbulence in the uniform flow made it possible to obtain stable solutions. For gentle flows produced around aerofoils at moderate angles of attack or aerofoils with a flap and slat at moderate deflection angles, the computed pressure distributions around the aerofoils and lift coefficients as well are in good agreement with measured results. The effectiveness of the turbulence model for such complicated flows was assured from this fact. For the flows which oscillated periodically or corresponded to aerofoils at high angles of attack, however, there was less agreement between computed and measured results. To solve a large-scale linear equation system, which was necessitated by the adoption of the implicit Euler scheme, a newly developed code for the direct method was used successfully. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0000880000 | |||||
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 TR-1316 |