Numerical Analysis Of Turbulence Mixing By Shockwave Interaction In Scramjet Combustor

Supersonic combustion ramjets or scramjets offer significant performance benefits over other propulsion technologies for atmospheric flights at hypersonic speeds, as a result of their ability to extract the oxygen for combustion from the atmosphere.Supersonic combustion in scramjet is still a challenging one. The complexity of supersonic combustion involves turbulent mixing, shock interaction and heat release in supersonic flow. This project deals with the enhancement of supersonic combustion by breaking down the streamwise vorticity and enhancing the rate of fuel air mixing in supersonic combustion. The amplification of stream wise vorticity is achieved out of the interaction between an oblique shock and fuel injector.