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 conferencePaperpeer-review

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
Country/TerritoryCanada
CityVancouver
Period10/4/0410/8/04

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Fingerprint

Dive into the research topics of 'Fundamental study of supersonic combustion in pure air flow with use of shock tunnel'. Together they form a unique fingerprint.

Cite this