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液体酸素・ガス水素ロケットの燃焼性能(Ⅰ)
https://jaxa.repo.nii.ac.jp/records/44726
https://jaxa.repo.nii.ac.jp/records/447262bc2774c-3019-4a0e-a82b-e40adb15eef2
名前 / ファイル | ライセンス | アクション |
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naltr00473.pdf (4.8 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 | 液体酸素・ガス水素ロケットの燃焼性能(Ⅰ) | |||||
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 Experimental Investigation of Combustion Performance of LOX/GH2 Rocket Combustor with Coaxial Injectors | |||||
著者 |
鈴木, 昭夫
× 鈴木, 昭夫× 八柳, 信之× 五味, 広美× 坂本, 博× SUZUKI, Akio× YATSUYANAGI, Nobuyuki× GOMI, Hiromi× SAKAMOTO, Hiroshi |
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著者所属 | ||||||
角田支所 | ||||||
著者所属 | ||||||
角田支所 | ||||||
著者所属 | ||||||
角田支所 | ||||||
著者所属 | ||||||
角田支所 | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, 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-473 巻 473, p. 26, 発行日 1976-09 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An experimental investigation of combustion performance was conducted in a LOX/GH2 rocket combustor with coaxial type injectors at a thrust level of 300 kgf with a nominal chamber pressure of 20 atm. The oxidant-fuel ratios ranged from approximately 2 to 10. The combustion chambers were of the segmented, heat-sink type. The chamber geometry varied in lengths from 11 to 26 cm and contraction rations of 2.03, 3.41 and 4.46, with a constant nozzle throat area. The injector had twelve coaxial elements with no recess and three replaceable faceplates having different hydrogen port areas. The attendant hydrogen-oxygen injection velocity ratio ranged from approximately 10 to 50. Observed C* efficiencies were correlated as a function of an equivalent chamber length, Le, in which the injection velocity ratio, VR, and the chamber length, L, are expressed as Le=L+αVR where α was considered nearly constant throughout the experiment. The correlation takes the form of ηc*=1-A exp(-BLe) where the constants A and B depend on the chamber contraction ratio. The variations of all experimental data from the relation were within approximately ± 1.8 percent. | |||||
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: NALTR0473000 | |||||
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-473 |