Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Tohoku University Graduate School of Engineering
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構研究開発報告
雑誌名(英)
JAXA Research and Development Report
巻
JAXA-RR-03-020E
発行年
2004-03-25
抄録（英）
Thrust performances of scramjet engines were compared with theoretical values to quantify the progress in engine performances (defined as achievement factors, or factors) from Mach (termed as M) 4 to M8 flight conditions. An engine with a ramp produced a net thrust of 215 N under the M8 tests and a comparison of a theoretical thrust yielded a thrust achievement factor of 51 percent. By excluding boundary layer, an engine with a thick strut delivered a net thrust of 560 N and showed a thrust factor of 92 percent and a net thrust factor of 45 percent. The thrusts were limited by flow separation caused by engine combustion (termed as engine unstart). The starting characteristics were improved by boundary layer controls in M6 and M4 conditions. An engine with a thin strut doubled the thrust from 1,620 N to 2,460 N by the boundary layer bleeding in the M6 tests. The improved thrust factor was 60 percent at the stoichiometric H2 condition. Under M4 tests, the net thrust was tripled by the bleed and a two-staged injection of H2. As results, the thrust factor was raised from 53 percent to 70 percent, the net thrust factor was increased from 32 percent to 55 percent. Studies required for improving the net performance were addressed.
Scramjet performance achieved in engine tests from M4 to M8 flight conditions
47412000.pdf
(2.94MB)
