关键词: 超声速冲压喷气发动机;双燃烧室;超音速燃速;动力装置;数值仿真

Abstract: The two dimensional,time dependent Navier Stokes equations were solved for supersonic flows of two parallel jets in a dual combustor.Numerical solution of these equations was accomplished with the flux split explicit finite difference algorithm of MacCormack.The Baldwin Lomax turbulent model was used for boundary flow and the mixing length model for shear layer.The numerical results are compared with experimental data,and the obtained results are better.Also the experiment shows that the effects of separation zone and the parameters of two supersonic flow jets on the wave pattern are significant.

Key words: Supersonic combustion ramjet engine;Daul combustor +;Supersonic combustion;Power plant;Numerical simulation