Numerical simulation of mixing and combustion flow-field in afterburning chamber for solid rocket ramjet

By using Renault averaged Navier-Stokes equation and k-ε turbulent combustion model, the mixing and combustion flow-field in afterburning chamber of a choked solid ramjet was numerically simulated. The effect of inlet size, inlet angle, dome height, primary nozzle expansion ratio and nozzle numbers on combustion efficiency were taken into account. The results indicate that the effects of inlet size and inlet angle on mixing and afterburning in chocked ramjet are the same as that in unchoked ramjet. Dispersity of gas flow can be enhanced and afterburning efficiency can be improved by increasing primary nozzle numbers and nozzle expansion ratio. The way improving afterburning efficiency was theoretically found.