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

Research output: Contribution to journalConference article

19 Citations (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)384-389
Number of pages6
JournalActa Astronautica
Volume57
Issue number2-8
DOIs
Publication statusPublished - Jul 1 2005
EventInfinite Possibilities Global Realities, Selectred Proceedings of the 55th International Astronautical Federation Congress, Vancouver -
Duration: Oct 4 2004Oct 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

Cite this

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.

In: Acta Astronautica, Vol. 57, No. 2-8, 01.07.2005, p. 384-389.

Research output: Contribution to journalConference 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. In: Acta Astronautica. 2005 ; Vol. 57, No. 2-8. pp. 384-389.
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