Numerical Modelling of Scramjet Combustor

  • M. Deepu N.S.S. College of Engineering, Palakkad
  • S. S. Gokhale Indian Institute of Technology Madras, Chennai
  • S. Jayaraj National Institute of Technology, Calicut
DOI: https://doi.org/10.14429/dsj.57.1784
Keywords: Scramjet, strut injector, supersonic combustor, reduced chemistry, point implicitmethod, FVM

Abstract

Numerical modelling of turbulent-reacting flow field of supersonic combustion ramjet(scramjet) combustors are presented. The developed numerical procedure is based on the implicittreatment of chemical source terms by preconditioning and solved along with unstedy turbulentNavier-Stokes equations explicitly. Reaction is modelled using an eight-step hydrogen-airchemistry. Code is validated against a standard wall jet experimental data and is successfullyused to model the turbulent-reacting flow field resulting due to the combustion of hydrogeninjected from diamond-shaped strut and also in the wake region of wedge-shaped strut placedin the heated supersonic airstream. The analysis could demonstrate the effect of interaction ofoblique shock wave with a supersonic stream of hydrogen  in its (fuel-air) mixing and reactionfor strut-based scramjet combustors.
Published
2007-07-01
How to Cite
Deepu, M., Gokhale, S., & Jayaraj, S. (2007). Numerical Modelling of Scramjet Combustor. Defence Science Journal, 57(4), 367-379. https://doi.org/10.14429/dsj.57.1784
Issue
Vol 57 No 4
Section
Aeronautical Systems
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