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ロケットエンジン高空性能試験用蒸気エゼクタの実験
https://jaxa.repo.nii.ac.jp/records/44820
https://jaxa.repo.nii.ac.jp/records/44820f7516e8d-1141-415e-a1c2-384bb0edc65b
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00566.pdf (1.1 MB)
|
|
| Item type | テクニカルレポート / Technical Report(1) | |||||
|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||
| タイトル | ||||||
| タイトル | ロケットエンジン高空性能試験用蒸気エゼクタの実験 | |||||
| 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 | Experiments on Steam Ejectors for Rocket Engine Altitude Simulation | |||||
| 著者 |
宮島, 博
× 宮島, 博× 山田, 晃× 木皿, 且人× 鎌田, 真× 佐藤, 政裕× 植野, 孝× 熊谷, 達夫× 日下, 和夫× MIYAJIMA, Hiroshi× YAMADA, AKIRA× KISARA, Katsuto× KAMATA, Makoto× SATO, Masahiro× UENO, Takashi× KUMAGAI, Tatsuo× KUSAKA, Kazuo |
|||||
| 著者所属 | ||||||
| 航空宇宙技術研究所角田支所 | ||||||
| 著者所属 | ||||||
| 宇宙開発事業団 | ||||||
| 著者所属 | ||||||
| 元・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 | ||||||
| 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（英） | ||||||
| en | ||||||
| Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||
| 著者所属（英） | ||||||
| en | ||||||
| National Space Development Agency of Japan(NASDA) | ||||||
| 著者所属（英） | ||||||
| en | ||||||
| Former 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 | ||||||
| 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-566 巻 566, p. 18, 発行日 1979-04 |
|||||
| 抄録（英） | ||||||
| 内容記述タイプ | Other | |||||
| 内容記述 | Ejector model tests were performed to determine possible configuration modifications of the two stage steam ejector of NAL’s rocket engine altitutde simulation test facility to obtain lower zero-secondary-flow capsule pressures. The loss of the suction performance, at high secondary flow, which is the result of modifications, should be minimal. The Configuration parameters which were tested, were ejector second throat area, relative distance of nozzle exit and diffuser inlet plane, nozzle area ratio, nozzle throat area, and ejector shroud geometry. Three configurations were selected for the final tests and satisfactory results were obtained on 1/8.6 linear scale models. The method of predicting the starting pressure ratio at zero secondary flow, which was developed by German et al., and the piecewise uniformity approach for predicting performance at high secondary flow, which was developed by Fabri et al., were shown to be useful as a guide. | |||||
| 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: NALTR0566000 | |||||
| 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-566 | |||||
