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垂直孔多孔壁の二次元揚力干渉に関する実験
https://jaxa.repo.nii.ac.jp/records/44817
https://jaxa.repo.nii.ac.jp/records/448178f895cdb-9df0-49e7-9269-7e074bdabef9
名前 / ファイル | ライセンス | アクション |
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naltr00563.pdf (1.4 MB)
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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 | 垂直孔多孔壁の二次元揚力干渉に関する実験 | |||||
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 | An Experiment of Lift Interference on 2-Dimensional Wings in a Wind Tunnel with Perforated Walls | |||||
著者 |
沢田, 秀夫
× 沢田, 秀夫× 三堀, 進× 佐藤, 衛× 鈴木, 弘一× 細江, 信幸× SAWADA, Hideo× MITSUBORI, SUSUMU× SATO, Mamoru× SUZUKI, Koichi× HOSOE, Nobuyuki |
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著者所属 | ||||||
航空宇宙技術研究所空気力学第二部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第二部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第二部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第二部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第二部 | ||||||
著者所属(英) | ||||||
en | ||||||
Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
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 TR-563 巻 563, p. 6, 発行日 1979-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An experiment on wall interference caused by the lift with two-dimensional wings, was carried out in the NAL 2m × 2m transonic wind tunnel with perforated walls, at high subsonic speeds. The open area ratios of upper and lower test section walls were set at 20%. Two airfoil models were used. In this experiment, pressure distributions near the upper and lower walls inside the test section were also measured, in addition to the pressure distribution on an airfoil model. Various quantities of lift interference with two-dimensional wings were assessed by a new method. This method was proposed in a previous paper, by one of the present authors, and requires only the measurement of pressure distributions on flow boundaries. Lift interference parameters, δ0 and δ1, for the present case, were evaluated indirectly by this method. | |||||
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: NALTR0563000 | |||||
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-563 |