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: 会議への寄与タイプ論文

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.

元の言語英語
ページ7166-7171
ページ数6
出版物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
カナダ
Vancouver
期間10/4/0410/8/04

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supersonic combustion
shock tunnels
air flow
airflow
Tunnels
tunnel
combustion
stagnation temperature
stagnation pressure
compressed air
supersonic nozzles
gas injection
Air
shock waves
charge coupled devices
penetration
shock
cameras
Compressed air
shock wave

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

これを引用

Aso, S., Hakim, A. N., Miyamoto, S., Inoue, K., & Tani, Y. (2004). Fundamental study of supersonic combustion in pure air flow with use of shock tunnel. 7166-7171. 論文発表場所 International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, カナダ.

Fundamental study of supersonic combustion in pure air flow with use of shock tunnel. / Aso, Shigeru; Hakim, Arif Nur; Miyamoto, Shingo; Inoue, Kei; Tani, Yasuhiro.

2004. 7166-7171 論文発表場所 International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, カナダ.

研究成果: 会議への寄与タイプ論文

Aso, S, Hakim, AN, Miyamoto, S, Inoue, K & Tani, Y 2004, 'Fundamental study of supersonic combustion in pure air flow with use of shock tunnel', 論文発表場所 International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, カナダ, 10/4/04 - 10/8/04 pp. 7166-7171.
Aso S, Hakim AN, Miyamoto S, Inoue K, Tani Y. Fundamental study of supersonic combustion in pure air flow with use of shock tunnel. 2004. 論文発表場所 International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, カナダ.
Aso, Shigeru ; Hakim, Arif Nur ; Miyamoto, Shingo ; Inoue, Kei ; Tani, Yasuhiro. / Fundamental study of supersonic combustion in pure air flow with use of shock tunnel. 論文発表場所 International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, カナダ.6 p.
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