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Shock Waves pp 959-963 | Cite as

An experimental study of supersonic combustion with incoming high temperature pure air stream obtained by shock tunnel

  • A. N. Hakim
  • S. Aso
  • S. Miyamoto
  • K. Toshimitsu
Conference paper

Abstract

An experimental study is conducted to investigate the phenomena of supersonic combustion by means of shock tunnel. By using shock tunnel, 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 430 microseconds. By schlieren method and CCD UV camera, the effects of injection pressure to flowfield and the combustion were investigated.

Keywords

Injection Pressure Supersonic Flow Circular Hole Stagnation Pressure Flow Duration 
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Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • A. N. Hakim
    • 1
  • S. Aso
    • 1
  • S. Miyamoto
    • 1
  • K. Toshimitsu
    • 1
  1. 1.Dept. of Aeronautics and AstronauticsKyushu UniversityJapan

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