Starting characteristics of hypersonic pre-cooled turbojet inlet

Takayuki Kojima, Hideyuki Taguchi, Hiroaki Kobayashi, Tetsuya Sato

研究成果: Conference contribution

1 被引用数 (Scopus)

抄録

In this study, bypass door area for the Hypersonic Precooled Turbojet Engine to restart the variable intake is estimated. Total pressure recovery and mass capture ratio of the variable air intake is acquired by the supersonic wind tunnel testing of the half scale intake model. Pressure loss and temperature effectiveness of the precooler is acquired by direct connect firing tests of the engine. Using these results, area of the bypass door by which the intake can start is estimated. The bypass door area to restart the intake depends on the precooler’s cooling capability. If the engine runs on liquid hydrogen, area of the bypass door is 1800mm2~2000mm2(Abyp_eng/A0=0.26~0.29). If the liquid nitrogen is used for the coolant of the precooler, area of the bypass door is 2600mm2~2700mm2(Abyp_eng/A0=0.37~0.39).

本文言語English
ホスト出版物のタイトル20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
出版社AIAA American Institute of Aeronautics and Astronautics
ISBN(印刷版)9781624103209
DOI
出版ステータスPublished - 2015
イベント20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 - Glasgow, United Kingdom
継続期間: 2015 7 62015 7 9

出版物シリーズ

名前20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015

Other

Other20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
国/地域United Kingdom
CityGlasgow
Period15/7/615/7/9

ASJC Scopus subject areas

  • 航空宇宙工学
  • 宇宙惑星科学
  • 制御およびシステム工学

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