Starting characteristics of hypersonic pre-cooled turbojet inlet

Takayuki Kojima, Hideyuki Taguchi, Hiroaki Kobayashi, Tetsuya Sato

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

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).

Original languageEnglish
Title of host publication20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
PublisherAIAA American Institute of Aeronautics and Astronautics
ISBN (Print)9781624103209
DOIs
Publication statusPublished - 2015
Event20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 - Glasgow, United Kingdom
Duration: 2015 Jul 62015 Jul 9

Publication series

Name20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015

Other

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

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science
  • Control and Systems Engineering

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