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 articlepeer-review

29 Citations (Scopus)


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
Issue number2-8
Publication statusPublished - Jul 2005
EventInfinite Possibilities Global Realities, Selectred Proceedings of the 55th International Astronautical Federation Congress, Vancouver -
Duration: Oct 4 2004Oct 8 2004

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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