Fundamental study of supersonic combustion in pure air flow with use of shock tunnel

Shigeru Aso, Arif Nur Hakim, Shingo Miyamoto, Kei Inoue, Yasuhiro Tani

研究成果: Contribution to conferencePaper査読

抄録

An experimental study using reflected type of shock tunnel has been conducted to investigate the phenomena of supersonic combustion. In the experiment, test air is compressed by reflected shock wave up to stagnation temperature of 2800 K and stagnation pressure of 0.35 MPa. Heated air is used as a reservoir gas of supersonic nozzle. Hydrogen is injected transversely through circular hole into freestream of Mach 2. Flow duration is 300 microseconds. Schlieren method and CCD UV camera is used to obtain information on the shock structures and the region of combustion. The effects of total pressure of injection gas to the fuel penetration and the region of combustion have been revealed.

本文言語英語
ページ7166-7171
ページ数6
出版ステータス出版済み - 12 1 2004
イベントInternational Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, カナダ
継続期間: 10 4 200410 8 2004

その他

その他International Astronautical Federation - 55th International Astronautical Congress 2004
国/地域カナダ
CityVancouver
Period10/4/0410/8/04

All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 宇宙惑星科学

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