Kakuta Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC)
Kakuta Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC)
Kakuta Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC)
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)), Sagamihara, Kanagawa Japan
抄録（英）
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.
内容記述
形態: カラー図版あり
形態: CD-ROM1枚
内容記述（英）
Physical characteristics: Original contains color illustrations
Note: One CD-ROM
Dual-mode作動時の燃焼器内流れ場の一次元模擬について
