The present study describes the numerical investigations concerning a fuel ($H_2$) or inert gas ($N_2$) stream issued between supersonic air and fuel stream.
The basic flow configuration consists of a plane, double shear/mixing layer flow. For the numerical solution, a fully conservative unsteady implicit $2^nd$ order time accurate sub-iteration method and a $2^nd$ order Total Variation Diminishing (TVD) scheme are used with the finite volume method (FVM). The results are consist of two categories ; inert gas stream issued between supersonic air and fuel stream , and fuel gas stream issued between supersonic air and fuel stream.
The numerical calculation has been carried out in case of 1,2, and 4mm thickness of middle stream.
Inert gas stream which has 2mm thickness and fuel gas stream which has 4mm thickness result in the broad combustion region.