Abstract: A supersonic combustion flow analysis model with shock train structure has been developed to support airbreathing hypersonic vehicle design optimization studies. The model solves a stiff set of ordinary differential equations coupled with the equations for finiterate chemistry to describe the aerothermodynamics of ignition and combustion process within the supersonic combustor. The Billig's shock train model is used to simulate upstream propagation of high pressure within the combustor. The calculation of H₂/air supersonic combustion flowfield in three typical combustors with “a constant-area section + an expansion section”, “backward-facing step”, “strut injection” is used to validate the supersonic combustion model. The results show that the model presented explains accurately physical chemistry phenomena in supersonic combustion flowfield. Comparison with experimental data shows that the pressure distribution calculated by new model is closer to the experimental result than the previous model without shock train structure.