The flow field structure and performance of dual-combustor ramjet (DCR) were investigated through direct-connected experiment and numerical simulations.Semi-global kinetic mechanism was adopted in the simulations.The simulated pressure distributions agreed with the experimental data.Results show that:rapid reaction occurs in the mixing-layer between central high-temperature fuel-rich gas and peripheral air

the thermal choked throat appears at the position of 0.9m

and the combustion efficiency reaches a relatively high level.A method of assessing performance according to experiment and numerical simulation was brought forward.Results show that:the performance of the DCR presented is good under the condition of Mach number is 4.0

altitude is 17km.When the equivalence ratio is 0.9

the internal thrust is 8.3kN and specific impulse is 12.29kN ·s/kg.However

increasing equivalence ratio leads to unstart of inlet.