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 conferencePaper

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 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.

Original languageEnglish
Pages7166-7171
Number of pages6
Publication statusPublished - Dec 1 2004
EventInternational Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, Canada
Duration: Oct 4 2004Oct 8 2004

Other

OtherInternational Astronautical Federation - 55th International Astronautical Congress 2004
CountryCanada
CityVancouver
Period10/4/0410/8/04

Fingerprint

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

Cite this

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. Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.

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 Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.

Research output: Contribution to conferencePaper

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', Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada, 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. Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.
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. Paper presented at International Astronautical Federation - 55th International Astronautical Congress 2004, Vancouver, Canada.6 p.
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