To investigate complex non-equilibrium hypersonic shock wave/turbulent boundary layer interaction flows,a turbu-lent Prandtl number correction model was proposed.The proposed turbulent Prandtl number correction model was evaluated by numerical simulation and theoretical analysis methods to the flows around hypersonic flat plate,compression corners at freestream Mach number 9.22.The comparison of numerical simulation results with experimental data and the Kays's turbulent Prandtl number model indicates that for hypersonic complex flows,the turbulent Prandtl number should be corrected.The pro-posed turbulent Prandtl number correction model,which is modified by turbulent non-equilibrium parameters,demonstrates more accurate skin pressure and heat flux compared to the original model and Kays's model,the maximum wall heat flux rela-tive error is less than 6%.
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