Combustor performance computing model based on lumped parameter equations was used to simulate the 1-D flow field in the isolator and combustor along with the critical area method. The simulation of mass flow matching between isolator and combustor at every mode in dual-mode scramjet was achieved

and the mechanism of mass flow matching was analyzed. The results show that at the non-separation supersonic mode and the separation supersonic mode

the mass flow matching between isolator and combustor is achieved by lowering the Mach number at the throat when the fuel mass flow increases in combustor

while at the transonic mode and the subsonic mode

it is achieved by increasing the total pressure at the throat when the fuel mass flow increases in combustor.