Interaction of shock waves with turbulent boundary layer can cause flow separation and high heat transfer in hypersonic flows. In this paper, we study the effect of thermal non-equilibrium on surface properties in a cone flare configuration for different Mach numbers. We employ the shock-strength dependent turbulence model proposed in our previous work and extend it to high freestream enthalpy flows over an axis-symmetric cone-flare geometry. It is found that the shock unsteadiness modified \(k-\omega \) turbulence model with thermal non-equilibrium effects gives the best match with experimental data for surface pressure and heat transfer.