A turbulent combustion modeling method combining the improved delayed detached eddy simulation (IDDES) model and the flamelet/progress variable (FPV) model is developed and then applied in the simulation of two supersonic combustors, namely the DLR supersonic combustor and the Gamba model combustor. Results show good agreement with the experiment, validating the accuracy of this method in supersonic combustion simulations. As a comparison, k-ω SST model combined with the FPV model is applied in the same cases. It is found that the simulation of k-ω SST model leads to larger deviations compared with that of the IDDES model, and the time cost of the IDDES model is only 3% more than that of the k-ω SST model. Moreover, the initial and boundary conditions of flamelet libraries are set to fixed values, thus can not account for the pressure and temperature variations in compressible flows. In response to this, a pressure and temperature correction of the FPV model is proposed and then applied in the DLR case. Results indicate that the correction method noticeably improves the accuracy of supersonic combustion simulations. Nomenclature Cp = specific heat coefficient at pressure constant C = progress variable h = specific enthalpy k = turbulent kinetic energy P = pressure Pr = Prandtl number Sc = Schmidt number T = temperature t = time Y = mass fraction Z = mixture fraction  = dissipation rate of turbulent kinetic energy  = dynamic viscosity  = density  = Scalar dissipation rate  = turbulent eddy frequency  = mass production rate Subscripts 0 = stagnation property i = species st = stoichiometric t = turbulent Superscripts

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