ロケットエンジン高空性能試験用蒸気エゼクタの実験

Material type: 文書・図像類

Author: 宮島, 博ほか

Publisher: 航空宇宙技術研究所

Publication date: 1979-04

Material Format: Digital

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Note (General)：: Ejector model tests were performed to determine possible configuration modifications of the two stage steam ejector of NAL’s rocket engine altitutde s...

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Material Type: 文書・図像類
Title: ロケットエンジン高空性能試験用蒸気エゼクタの実験
Author/Editor: 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
Author Heading: 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
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1979-04
Publication Date (W3CDTF): 1979-04
Alternative Title: Experiments on Steam Ejectors for Rocket Engine Altitude Simulation
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-566
No. or year of volume/issue: 566
Volume: 566
Pages: 18-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): 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.
資料番号: NALTR0566000
レポート番号: NAL TR-566
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ