Numerical simulation of unsteady flow field on shock-induced combustion

K. Suzuki, A. Matsuo

Research output: Contribution to conferencePaperpeer-review

1 Citation (Scopus)


A three-dimensional numerical analysis that used two-step chemical reaction model was conducted on the unsteady combustion phenomenon around the supersonic flight body . Regular regime is a very steady mode, and the flow field where axisymmetric was strong. Influence of the grid resolution to the flow field was small. In Large-disturbance regime, the flow field was greatly changed by the changing the projectile diameter. The strength of the reaction shock was so strong that the reaction shocks interacted and distorted the leading bow shock wave strongly. Characteristic phenomena was observed in front of the projectile. Moreover, it has been understood that the flow field, greatly influences the grid resolution, exists.

Original languageEnglish
Publication statusPublished - 2009 Jan 1
Event7th Asia-Pacific Conference on Combustion, ASPACC 2009 - Taipei, Taiwan, Province of China
Duration: 2009 May 242009 May 27


Conference7th Asia-Pacific Conference on Combustion, ASPACC 2009
Country/TerritoryTaiwan, Province of China


  • Instability combustion oscillation
  • Numerical simulation
  • Shock-induced combustion

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Energy Engineering and Power Technology
  • Fuel Technology
  • Chemical Engineering(all)


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