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非定常運動をする二次元翼まわりの流れの離散渦法による計算
https://jaxa.repo.nii.ac.jp/records/43334
https://jaxa.repo.nii.ac.jp/records/43334cf9c1fd6-9f94-46e7-82de-0152b3a96677
名前 / ファイル | ライセンス | アクション |
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nalsp0010005.pdf (415.2 kB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 非定常運動をする二次元翼まわりの流れの離散渦法による計算 | |||||
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_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 | Numerical Calculation of Separated Flows Around a Wing Section at Unsteady Motion by a Discrete Vortex Method | |||||
著者 |
麻生, 茂
× 麻生, 茂× 二ツ寺, 直樹× 藤本, 淳× 林, 正徳× Aso, Shigeru× Futatsudera, Naoki× Fujimoto, Atsushi× Hayashi, Masanori |
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著者所属 | ||||||
九州大学工学部航空工学科 | ||||||
著者所属 | ||||||
九州大学工学部航空工学科 | ||||||
著者所属 | ||||||
三菱重工業株式会社 | ||||||
著者所属 | ||||||
西日本工業大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Aeronautical Engineering, Kyushu University | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Aeronautical Engineering, Kyushu University | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Heavy Industries Co.Ltd. | ||||||
著者所属(英) | ||||||
en | ||||||
Nishinippon Institute of Technology | ||||||
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 SP-10 巻 10, p. 27-32, 発行日 1989-11 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Separated flows around a wing section at unsteady motion are simulated numerically by a discrete vortex method combined with a panel method. The potential flows around wing sections is expressed by vortex sheets and separated shear layers are expressed by discrete vortices. In the calculation a separation point is determined by solving boundary layer equation. The strength of shed vortex is estimated using local velocity near separation point. Also modification for the estimation of pressure coefficients around wing section are proposed. The estimated pressure distributions show good agreements with experimental results. At first calculations are carried out for a wing section at fixed angle of attack. The results show excellent agreements with experiments. Secondly separated flows around pitching airfoils are simulated. A histerisis of lift of airfoil at dynamic stall is obtained in the calculation. Those results suggest that the present method is quite useful to simulate separated flows around wing section both at steady and unsteady motions. | |||||
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: NALSP0010005 | |||||
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-10 |