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衝撃波を伴わない遷音速翼型の実験
https://jaxa.repo.nii.ac.jp/records/45041
https://jaxa.repo.nii.ac.jp/records/45041d3a0a587-0455-4fbe-880c-1a8385c6679f
名前 / ファイル | ライセンス | アクション |
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naltr00783.pdf (1.1 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 | 衝撃波を伴わない遷音速翼型の実験 | |||||
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 | Experiment of a Schockless Transonic Airfoil | |||||
著者 |
中村, 正義
× 中村, 正義× 鈴木, 弘一× 中村, 正剛× 白井, 正孝× NAKAMURA, Masayoshi× SUZUKI, Koichi× NAKAMURA, Seigou× SHIRAI, Masataka |
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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(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-783 巻 783, p. 8, 発行日 1983-10 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An experiment was carried out on transonic flows over an airfoil which was partially modified from an arbitrary airfoil. The modification was made to satisfy the shockless condition which predicted on NAL TR-602, TR-602T. Static pressure were measured at 88 points on the airfoil surface, when the test Mach number was 0.5~0.8, the test angle of attack was 0deg~4deg and the Reynolds number was 4.0~4.6×10(exp 6). A schockless transonic flow was observed under a test condition close to the design condition. The supersonic region extends from 0.3% to 63% of airfoil chord length and the local maximum Mach number is 1.36. The result of this experiment supports the artificial flow method for obtaining shockless transonic airfoils which are partially modified from an arbitrary airfoil. | |||||
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: NALTR0783000 | |||||
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-783 |