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Thrust augmentation through after-burning in scramjet nozzles

  • Candon, Michael J. (School of Aerospace, Mechanical and Manufacturing Engineering, RMIT University) ;
  • Ogawa, Hideaki (School of Aerospace, Mechanical and Manufacturing Engineering, RMIT University) ;
  • Dorrington, Graham E. (School of Aerospace, Mechanical and Manufacturing Engineering, RMIT University)
  • Received : 2014.09.24
  • Accepted : 2014.11.22
  • Published : 2015.04.25
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Abstract

Scramjets are a class of hypersonic airbreathing engine that are associated with realizing the technology required for economical, reliable access-to-space and high-speed atmospheric transport. After-burning augments the thrust produced by the scramjet nozzle and creates a more robust nozzle design. This paper presents a numerical study of three parameters and the effect that they have on thrust augmentation. These parameters include the injection pressure, injection angle and streamwise injection position. It is shown that significant levels of thrust augmentation are produced based upon contributions from increased pressure, mass flow and energy in the nozzle. Further understanding of the phenomenon by which thrust augmentation is being produced is provided in the form of a force contribution breakdown, analysis of the nozzle flowfields and finally the analysis of the surface pressure and shear stress distributions acting upon the nozzle wall.

Keywords

References

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