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アイテム
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空気吸込ロケットの研究(III)-超音速モード燃焼器-
https://jaxa.repo.nii.ac.jp/records/45014
https://jaxa.repo.nii.ac.jp/records/45014d606fa58-5a02-42b5-aa41-da1edc8f557a
名前 / ファイル | ライセンス | アクション |
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naltr00756.pdf (1.3 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 | 空気吸込ロケットの研究(III)-超音速モード燃焼器- | |||||
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 | A Study of Air Breathing Rockets(III)-Supersonic Mode Combustors- | |||||
著者 |
升谷, 五郎
× 升谷, 五郎× 鎮西, 信夫× 工藤, 賢司× 村上, 淳郎× 小室, 智幸× 石井, 進一× MASUYA, Goro× CHINZEI, NOBUO× KUDO, Kenji× MURAKAMI, Atsuo× KOMURO, Tomoyuki× ISHII, Shinichi |
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著者所属 | ||||||
航空宇宙技術研究所角田支所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所角田支所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所角田支所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所角田支所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所角田支所 | ||||||
著者所属 | ||||||
元・航空宇宙技術研究所角田支所 | ||||||
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) | ||||||
著者所属(英) | ||||||
en | ||||||
Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Former 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-756 巻 756, p. 19, 発行日 1983-04 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An experimental study was made on supersonic mode combustors of an air breathing rocket engine. Supersonic streams of room-temperature air and hot fuel-rich rocket exhaust were coaxially mixed and burned in a conically diverging duct of 2deg half-angle. The effect of air inlet Mach number and excess air ratio was investigated. Axial wall pressure distribution was measured to calculate one dimensional change of Mach number and stagnation temperature. Calculated results showed that supersonic combustion occurred in the duct. At the exit of the duct, gas sampling and Pitot pressure measurement was made, from which radial distributions of various properties were deduced. The distribution of mass fraction of elements from rocket exhaust showed poor mixing performance in the supersonic mode combustors compared with the previously investigated cylindrical subsonic mode combustors. Secondary combustion efficiency correlated well with the centerline mixing parameter, but not with Annushkin’s non-dimensional combustor length. No major effect of air inlet Mach number or excess air ratio was seen within the range of conditions under which the experiment was conducted. | |||||
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: NALTR0756000 | |||||
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-756 |