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並進振動する楕円翼まわりの非定常粘性流れ(その1 数値解析)
https://jaxa.repo.nii.ac.jp/records/32278
https://jaxa.repo.nii.ac.jp/records/3227822fc78bd-4375-433e-a788-9d63e638a20f
名前 / ファイル | ライセンス | アクション |
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SA0125447.pdf (2.7 MB)
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Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 並進振動する楕円翼まわりの非定常粘性流れ(その1 数値解析) | |||||
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_6501 | |||||
資源タイプ | departmental bulletin paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Unsteady viscous flow around an oscillating elliptic aerofoil | |||||
著者 |
岡島, 厚
× 岡島, 厚× 浅沼, 強× 高田, 浩之× OKAJIMA, Atsushi× ASANUMA, Tsuyoshi× TAKATA, Hiroyuki |
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著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeroautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeroautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeroautical Science University of Tokyo | ||||||
出版者 | ||||||
出版者 | 東京大学宇宙航空研究所 | |||||
書誌情報 |
東京大学宇宙航空研究所報告 巻 7, 号 3, p. 605-654, 発行日 1971-07 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 翼まわりの非定常流れに関する研究の一環として,一様粘性流れの中におかれた静止,または振動する楕円翼(翼厚比20%と50%)まわりの流れを,数値解法によって解き,レイノルズ数Re=40~80,翼の迎え角α=O°~20°,翼の無次元振動数k=O~1.4の範囲に対する流線や済度分布を求めた.ついで,これらの計算結果から振動する翼に働く圧力分布,粘性せん断力分布そして法線力,接線力やモーメントを求めた.とくに流体の粘性効果の観点から,変動流体力に関連の深い翼面上のよどみ点やはく難点などの挙動,すなわちそ`れらの移動振幅や位相差などを明らかにすることができた. | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | To furnish some fundamental information about the viscous effect of flow in the phenomena of unsteady flow such as flutter and rotating stall in turbomachinery, we numerically solve the Navier-Stokes equations for the flow around the stationary or oscillating elliptic aerofoil, the thickness ratio of which is 20% or 50%. Flow configurations, pressure and viscous shear stress distributions and aerodynamic forces are obtained in the ranges of Reynolds number .Re=40~80, angle of attack α=0°~20° and reduced frequency k = 0~1.4. Concerning the viscous effect of fluid on the aerodynamic forces, the behavior of points of flow stagnation and separation on the aerofoil is examined and found to have a close relationship to the unsteady forces. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0563-8100 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00161914 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0125447000 |