@techreport{oai:jaxa.repo.nii.ac.jp:00044820,
 author = {宮島, 博 and 山田, 晃 and 木皿, 且人 and 鎌田, 真 and 佐藤, 政裕 and 植野, 孝 and 熊谷, 達夫 and 日下, 和夫 and MIYAJIMA, Hiroshi and YAMADA, AKIRA and KISARA, Katsuto and KAMATA, Makoto and SATO, Masahiro and UENO, Takashi and KUMAGAI, Tatsuo and KUSAKA, Kazuo},
 month = {Apr},
 note = {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},
 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},
 year = {1979}
}