@inproceedings{oai:jaxa.repo.nii.ac.jp:00016613,
 author = {富岡, 定毅 and 齋藤, 俊仁 and 谷, 香一郎 and Tomioka, Sadatake and Saito, Toshihito and Tani, Koichiro},
 book = {宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium},
 month = {Jan},
 note = {平成21年度宇宙輸送シンポジウム(2010年1月14日-15日, 宇宙航空研究開発機構宇宙科学研究本部), Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)),  Sagamihara, Kanagawa Japan, A modification of the one-dimensional simulation was carried out to simulate pressure recovery due to pseudo-shock-wave system in a rocket-based combined cycle engine's combustor under dual-mode operation. So-called two flow-tubes model was employed to express the pseudo-shock-wave system observed in the engine tests. The rocket exhaust plume at a very reduced output experienced a pressure recovery to the airflow pressure, decelerated to subsonic speed. This decelerated flow was named as the low-speed flow in the two flow-tubes model. The high-speed airflow decelerated by its own while a linear portion of it was entrained into the low-speed flow, until the whole high-speed flow was entrained at the secondary fuel injector location. The modified simulation could express the gradual pressure recovery associated with the pseudo-shock-wave system, however, the resulting pressure level was higher than the measurement. The incomplete mixing in the experiment ought to the discrepancy., 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: AA0064741043},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {Dual-mode作動時の燃焼器内流れ場の一次元模擬について},
 volume = {平成21年度},
 year = {2010}
}