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前縁半径の小さい単独翼廻りの2次元粘性流解析コードの検証
https://jaxa.repo.nii.ac.jp/records/43325
https://jaxa.repo.nii.ac.jp/records/43325213576d0-00f0-497a-b5bd-b6ee246b94c9
名前 / ファイル | ライセンス | アクション |
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nalsp0009034.pdf (388.6 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 | 前縁半径の小さい単独翼廻りの2次元粘性流解析コードの検証 | |||||
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 | Verification of 2D-Viscous Flow Simulation Codes Using Airfoil with Very Small Leading Edge Radius | |||||
著者 |
福田, 正大
× 福田, 正大× 中橋, 和博× 廣瀬, 直喜× 河合, 伸坦× 菊野, 栄次× Fukuda, Masahiro× Nakahashi, Kazuhiro× Hirose, Naoki× Kawai, Nobuhiro× Kikuno, Eiji |
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著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
住友精密工業 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
Sumitomo Precision Products Co., Ltd | ||||||
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-9 巻 9, p. 229-234, 発行日 1988-12 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In recent years, numerical simulation method based on viscous equation is widely applied to aerodynamic research and development in the field of airfoil, wing, fuselage, etc. It is proved powerful, and the application of this method to propellar blades research and development, especially for the ATP-blades, is natural. While many experiences with two-dimensional viscous simulation for thick airfoils are accumulated, however experience for such thin airfoils with very sharp leading edge as often propeller blades have the characteristics is relatively few. The verification of the two-dimensional viscous simulation codes, NSFOIL and NS2D applied to one of those airfoils, NACA 16-204 airfoil which was tested by the two-dimensional wind tunnel at NAL last year, is main object of the present report. Mach number sweeps at low angles of attack and angle of attack sweeps at M=0.6 and 0.85 were made. The comparison of the computed aerodynamic characteristics with the wind tunnel data assure us that the method is useful in this field, although some improvements of the codes are to be desired. | |||||
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: NALSP0009034 | |||||
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-9 |