Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
National Space Development Agency of Japan(NASDA)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
Technical Report of National Aerospace Laboratory TR-848T
The effective specific impulse of secondary flow injected into a supersonic portion of a large-area ratio nozzle was evaluated experimentally. An oxygen/hydrogen thrust chamber with a 4000N thrust level and a chamber pressure of 3.5MPa was used. The secondary flow (ambient temperature hydrogen as a simulant of the oxygen/hydrogen turbine exhaust gas mixture) was injected through 30 discrete holes at a 13:1 local area ratio into a nozzle with a 140:1 overall area ratio. The mass flow ratio of secondary flow to primary flow was varied from 1 to 5％. Using a simple theory, experimentally obtained effective secondary flow specific impulse Is was compared with calculated results. The experimental Is value was consistently higher than the calculated value by about 20％, presumably because of mixing and heat transfer effects which were not taken into account in the theoretical calculation. The secondary flow film cooling effect was substantial and persisted up to the nozzle exit.
Effective Specific Impulse of Secondary Flow Injected into a Rocket Nozzle
naltr0848t.pdf
(973.62KB)
