@techreport{oai:jaxa.repo.nii.ac.jp:00044700,
 author = {宮島, 博 and 日下, 和夫 and 阿部, 登 and 鎌田, 真 and 植野, 孝 and 佐藤, 政裕 and MIYAJIMA, Hiroshi and KUSAKA, Kazuo and ABE, Noboru and KAMATA, Makoto and UENO, Takashi and SATO, Masahiro},
 month = {Mar},
 note = {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., 資料番号: NALTR0449000, レポート番号: NAL TR-449},
 title = {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},
 year = {1976}
}