| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
ロケットエンジン高空性能試験用エゼクタの実験的研究 |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
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資源タイプ |
technical report |
| その他のタイトル（英） |
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その他のタイトル |
Experimental Study of Zero-Secondary-Flow Ejectors for Rocket Engine Altitude Simulation |
| 著者 |
宮島, 博
日下, 和夫
阿部, 登
鎌田, 真
植野, 孝
佐藤, 政裕
MIYAJIMA, Hiroshi
KUSAKA, Kazuo
ABE, Noboru
KAMATA, Makoto
UENO, Takashi
SATO, Masahiro
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| 著者所属 |
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角田支所 |
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角田支所 |
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角田支所 |
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角田支所 |
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角田支所 |
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角田支所 |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
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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-449
巻 449,
p. 18,
発行日 1976-03
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
Ejector characteristics tests and detailed diffuser wall pressure measurements were made on six basic zero secondary flow ejector configurations, which were combinations of two different area ratio nozzles and three diffusers. One constant area diffuser and two second throat diffusers with different contraction area ratios were used. In each configuration, a diffuser was attached to a vacuum capsule in which a simulated rocket engine nozzle driven by cold nitrogen gas was set up. It is shown that over a certain range of nozzle exit position XNE relative to the second throat diffuser inlet plane, a minimum capsule pressure ratio Pc/Pt is maintained and that the optimum position, i.e., the nozzle exit position where minimum starting or break down system pressure ratio Pt/Pa is minimum, is somewhere in the capsule region. A further withdrawal of the nozzle into the capsule region produces an increase in capsule pressure ratio which is approximately linear with XNE. In a better performing configuration, the length of separated flow region is shorter for the same system pressure ratio. The starting characteristics data and second throat ramp pressures are compared with the calculation using the approximate method of German, et al., and it is shown that the method predicts generally satisfactory trends when the relative position of nozzle and diffuser is appropriate. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0389-4010 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: NALTR0449000 |
| レポート番号 |
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内容記述タイプ |
Other |
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内容記述 |
レポート番号: NAL TR-449 |
naltr00449.pdf (2.5 MB)
