Volume 26 Issue 8
Aug.  2011
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FAN Zhou-qin, SUN Ming-bo, LIU Wei-dong. Flamelet/progress variable model for supersonic reacting flows[J]. Journal of Aerospace Power, 2011, 26(8): 1750-1755.
Citation: FAN Zhou-qin, SUN Ming-bo, LIU Wei-dong. Flamelet/progress variable model for supersonic reacting flows[J]. Journal of Aerospace Power, 2011, 26(8): 1750-1755.
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Flamelet/progress variable model for supersonic reacting flows

  • College of Aerospace and Materials Engineering, National University of Defense Technology,Changsha 410073,China

  • Received Date: 2010-07-21
  • Rev Recd Date: 2010-10-13
  • Publish Date: 2011-08-28
    Abstract
  • The flamelet/progress variable model for supersonic turbulent reacting flows was developed based on Pierce's model for low Mach number flows,in consideration of the compressibility effects and shock waves.The present model solved the mixture fraction and progress variable transport equations,and employed three solution branches of flamelet equation:the steady burning branch,the unstable branch of partially extinguished states and the complete extinction state.The performance of the flame/progress variable model was compared to the steady flamelet model for predicting the product and temperature field of a hydrogen-air supersonic combustion ramjet engine in DLR (Deutsches Zentrum für Luft- und Raumfahrt) for which experimental data are available.With capturing of extinction and lifted flame,the present model is good agreement with the experimental data,and outperforms the steady flamelet model which predicts an attached flame.

     

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