Numerical simulations were carried out for a mixing enhancement measure-streamwise surge plus low velocity flow inlet-for specific supersonic mixing layer in dual combustor ramijet's(DCR's) supersonic combustor.The results show that

if streamwise surge is added at low velocity flow inlet

the positive impact on mixing enhancement is evident

and the burning intensity is increased

however it still belongs to weak combustion.The frequency determines the location and scale of vortices assembling region

and the swing determines uniform degree of distributed and assembled vortices.