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USB方式STOL機のエンジン艤装(I) 円型合流ダクトによるエンジンマッチング特性(その1)
https://jaxa.repo.nii.ac.jp/records/44960
https://jaxa.repo.nii.ac.jp/records/449609b5ffe43-aaeb-4b06-8773-82b42b8d1a1d
名前 / ファイル | ライセンス | アクション |
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naltr00703.pdf (1.2 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 | USB方式STOL機のエンジン艤装(I) 円型合流ダクトによるエンジンマッチング特性(その1) | |||||
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 Engine Installation for Fan Jet STOL Aircraft using USB powered High Lift System(I) Engine Matching Test for Circular Confluent Exhaust Duct | |||||
著者 |
松木, 正勝
× 松木, 正勝× 鳥崎, 忠雄× 近藤, 博× 中山, 晋× 関根, 静雄× 吉田, 晃× 森田, 光男× 越沼, 威× 松田, 幸雄× 藤沢, 良昭× 吉田, 公則× MATSUKI, Masakatsu× TORISAKI, Tadao× KOND0, Hiroshi× NAKAYAMA, Susumu× SEKINE, Shizuo× YOSHIDA, Akira× MORITA, Mitsuo× KOSHINUMA, Takeshi× MATSUDA, Yukio× FUJISAWA, Yoshiaki× YOSHIDA, Masanori |
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著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所航空機公害研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
川崎重工業株式会社 | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Noise and Emission Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kawasaki Heavy Industries, 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報告 en : Technical Report of National Aerospace Laboratory TR-703 巻 703, p. 15, 発行日 1982-02 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Purposes of this research are to obtain design data of an engine-nacelle for a USB powered high lift system on a STOL aircraft, which is being developed by the National Aerospace Laboratory. In these design data, structure and strength of the engine-nacelle and conformity between an engine and its engine-nacells are the most important problems. In order to obtain engine operational characteristics for mixing a fan and a core flow, a test was performed using a FJR 710 turbo-fan engine installed in a circular confluent exhaust duct. Test parameters of interest are the length of the mixing zone and the contraction of the mixing nozzle. As a result of this investigation, it has been proved that a power-turbine output decreases with an increase of outlet pressure of the power-turbine due to the mixing. And a clue to a design method to correct engine operational matching characteristics was found. | |||||
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: NALTR0703000 | |||||
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-703 |