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titleScramjet performance achieved in engine tests from M4 to M8 flight conditions
Other TitleM4からM8におけるスクラムジェットエンジン試験における性能達成度
Author(jpn)三谷 徹; 富岡 定毅; 苅田 丈士; 鎮西 信夫; 河内 俊憲
Author(eng)Mitani, Toru; Tomioka, Sadatake; Kanda, Takeshi; Chinzei, Nobuo; Kochi, Toshinori
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 東北大学 大学院工学研究科
Author Affiliation(eng)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
Issue Date2004-03-25
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication date2004-03-25
Languageeng
AbstractThrust 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.
DescriptionJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
Keywordsscramjet engine; performance test; Mach number; boundary layer; thrust; air capture ratio; stoichiometric ratio; スクラムジェットエンジン; 性能試験; マッハ数; 境界層; 推力; 空気捕捉比; 化学量論比
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1148
SHI-NOAA0047412000
Report NoJAXA-RR-03-020E
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/30876


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