@inproceedings{oai:jaxa.repo.nii.ac.jp:00016453,
 author = {久保, 貴裕 and 富岡, 定毅 and 谷, 香一郎 and 櫻中, 登 and Kubo, Takahiro and Tomioka, Sadatake and Tani, Koichiro and Sakuranaka, Noboru},
 book = {平成22年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2010},
 month = {},
 note = {平成22年度宇宙輸送シンポジウム(2011年1月20-21日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Aerodynamic tests of small scale rocket combined cycle engine models were carried out to evaluate their performance and at rocket mode operation. In the experiment, thrust force of four models was measured on condition that environmental pressure was set up 4 kPa, rocket chamber pressure ranged up to 3MPa. Nitrogen gas was exhausted as the substitution for the actual rocket gas. As a result, thrust force of four models differentiated and thrust force of rocket combined cycle engine was lower than that of calculated value of conical rocket nozzle. Flow structures of rocket combined cycle engine nozzle were investigated to discuss the performance variation., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065073006},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {RBCCエンジンのノズル特性について},
 year = {2011}
}