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軸対称エアインテークの風洞試験による性能評価
https://jaxa.repo.nii.ac.jp/records/33346
https://jaxa.repo.nii.ac.jp/records/333460cfade47-ad52-4e64-8fb8-f9410f5b405b
名前 / ファイル | ライセンス | アクション |
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SA0200119.pdf (776.5 kB)
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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 | 軸対称エアインテークの風洞試験による性能評価 | |||||
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 | Wind Tunnel Tests of the Axisymmetric Air Intake | |||||
著者 |
小島, 孝之
× 小島, 孝之× 小林, 弘明× 佐藤, 哲也× Kojima, Takayuki× Kobayashi, Hiroaki× Sato, Tetsuya |
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著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science (ISAS) | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science (ISAS) | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science (ISAS) | ||||||
出版者 | ||||||
出版者 | 宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science | |||||
書誌情報 |
宇宙科学研究所報告. 特集: ATREXエンジンの研究開発 巻 46, p. 133-144, 発行日 2003-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Experimental Study of a variable geometry axisymmetric air intake (inlet) for ATREX engine has been done at ISAS supersonic wind tunnel and NASA GRC 1-by 1-foot supersonic wind tunnel since 1993. More than 13knds of subscale intake models whose cowl inlet diameter is 123 mm are tested and intake aerodynamic performances such as total pressure recovery and mass capture ratio are obtained. Each intake has the peculiar characteristics such as high mass capture type, high total pressure type. Some of these intakes attained the target of the development study from the viewpoint of intake aerodynamic performances at the limited Mach number range. The configuration of the supersonic diffuser passage is designed using the computer program that employs the method of characteristics and the configuration of the subsonic diffuser passage is designed using the axisymmetric CFD. The performances under off-design condition are also investigated by the CFD in parallel with the wind tunnel tests. By several trials of design and tests, intake design method was established. Furthermore off-design performances such as the bleed pattern of the spike and the cowl, the shape of the spike and the cowl tip, spike boundary layer transition point, and the angle of attack are investigated. And several proposals to improve the aerodynamic performances are done. Because the boundary layer on the spike is thicker than the cowl, bleed from the spike is more important to improve the total pressure recovery. A boundary layer transition system at the tip of the spike is necessary for the flyable intake model. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0285-9920 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00354485 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0200119000 |