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<論文>遷音速回転翼列試験機ならびに高速環状翼列風洞設備について(高速内部流体実験施設報告)
https://jaxa.repo.nii.ac.jp/records/31471
https://jaxa.repo.nii.ac.jp/records/3147137b6e348-20b4-4a9f-a3de-21bbc49a00cd
名前 / ファイル | ライセンス | アクション |
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SA0124357.pdf (1.7 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 | <論文>遷音速回転翼列試験機ならびに高速環状翼列風洞設備について(高速内部流体実験施設報告) | |||||
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 | High Speed Annular Cascade Wind Tunnel and Transonic Axial Flow Test Compressor | |||||
著者 |
田中, 英穂
× 田中, 英穂× 丸田, 秀雄× 八田, 桂三× 網野, 一夫× TANAKA, Hideo× MARUTA, Hideo× HATTA, Keizo× AMINO, Kazuo |
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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 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeronautical Science, University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeronautical Science, University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeronautical Science, University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeronautical 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 1, 号 4_B, p. 451-469, 発行日 1965-12 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | After the completion of the air source system symbolized by the 10 m sphere reservoir, it has become very easy to get much amount of high speed air flow. Thereupon making use of this air source system, facility having two functions of high speed annular cascade wind tunnel and transonic axial flow test compressor has been constructed. This facility, only by exchanging a part of test section (inner casing, rotor, etc.), is used as the above mentioned two installations. Its specifications are as follows: 1) High speed annular cascade wind tunnel. Type: blow down type, Testsection: outer diametr 350 mm, boss ratio 0.4, Mach number: M= 1.0, Running time: about 4 min. (with M=1.0 and exit pressure of 1.0ata.). 2) Transonic axial flow test compressor. Outer diameter: 350 mm, Boss ratio: 0.7 at inlet section, Number of stage: 1, Rotational speed: 19090 rpm, Compression ratio: 1.6, Axial air velocity: 180 m/s, Relative Mach number: 1.12 at tip section of moving blade, Blade shape: double circular arc, Driving svstem: 500 KW AC motor and 400 PS air turbine. | |||||
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: SA0124357000 |