The calculation of H2/air supersonic combustion flowfield in a typical combustor with "a constant-area section + an expansion section" was carried out with three methods: quasi-one-dimensional flow model

axisymmetric and three-dimensional Reynolds-averaged Navier-Stokes Solver.The hydrogen/air mechanism of 13 species and 32 reactions was used.The study shows that the quasi-one-dimensional flow model and three-dimensional Navier-Stokes Solver are effective for predicting the distribution of the parameters in the supersonic combustor.Good agreement is achieved between the calculated and experimental static pressure data except the precombustion shock train region.The quasi-one-dimensional flow model coupled with the finite-rate chemistry equations provides a rapid methodology with strong adoptability for performance prediction.The three-dimensional numerical simulation could depict the detailed information in the flow

but it will take up a great deal of time.Given different advantages

these two models would be used in different design phases of supersonic combustor.