Scramjet performance achieved in engine tests from M4 to M8 flight conditions

Tohru Mitani, Sadatake Tomioka, Takeshi Kanda, Nobuo Chinzei, Toshinori Kouchi

研究成果

33 被引用数 (Scopus)

抄録

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%. By excluding boundary layer, an engine with a thick strut delivered a net thrust of 560 N and showed a thrust factor of 92% and a net thrust factor of 45%. The thrusts were limited by flow separation caused by engine combustion (termed as "engine unstart"). The starting characteristics was improved by boundary layer controls in M6 and M4 conditions. An engine with a thin strut doubled the thrust from 1620 N to 2460 N by the boundary layer bleeding in the M6 tests. The improved thrust factor was 60% 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% to 70%, the net thrust factor was increased from 32% to 55%. Studies required for improving the net performance was addressed.

本文言語English
ホスト出版物のタイトル12th AIAA International Space Planes and Hypersonic Systems and Technologies
出版ステータスPublished - 12月 1 2003
外部発表はい
イベント12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003 - Norfolk, VA
継続期間: 12月 15 200312月 19 2003

出版物シリーズ

名前12th AIAA International Space Planes and Hypersonic Systems and Technologies

Other

Other12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003
国/地域United States
CityNorfolk, VA
Period12/15/0312/19/03

ASJC Scopus subject areas

  • 宇宙惑星科学
  • 航空宇宙工学
  • 制御およびシステム工学

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