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: ジャーナルへの寄稿Conference article

19 引用 (Scopus)

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 μs. Schlieren method and CCD UV camera are 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 obtained.

元の言語英語
ページ(範囲)384-389
ページ数6
ジャーナルActa Astronautica
57
発行部数2-8
DOI
出版物ステータス出版済み - 7 1 2005
イベントInfinite Possibilities Global Realities, Selectred Proceedings of the 55th International Astronautical Federation Congress, Vancouver -
継続期間: 10 4 200410 8 2004

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Tunnels
Air
Compressed air
Charge coupled devices
Shock waves
Mach number
Nozzles
Cameras
Hydrogen
Gases
Experiments
Temperature

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

これを引用

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.

:: Acta Astronautica, 巻 57, 番号 2-8, 01.07.2005, p. 384-389.

研究成果: ジャーナルへの寄稿Conference article

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. :: Acta Astronautica. 2005 ; 巻 57, 番号 2-8. pp. 384-389.
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