[14] used the [PERSON] 5-species, 7-species, 11-species chemical reaction models and one-temperature, two-temperature thermodynamic models to solve the thermochemical nonequilibrium flow, respectively, and found that the differences between the heat flux distributions predicted by the 7-and 11-species was not significant, while the heat flux of the 5-species was smaller, with a difference up to 10% or even more; the heat fluxes calculated by different thermodynamic models are slightly different, with a maximum difference of about 10%. [PERSON] et al. [15] compared the aerodynamic heat fluxes under the [PERSON] 5-, 7-, 11-species chemical reaction models and found that the wall heat fluxes under the 7- and 11-species were significantly larger than that of the 5-species when the Mach number was greater than 12, and that the 7-species model should be adopted. [PERSON] et al. [16] used the Gupta 5-species and Park 5-species chemical kinetic models to solve the nearly same results of the air compositions at the stagnation point of a sphere. However, the difference between the shock standoff distances calculated with perfect gas and chemical reaction gas is significant. [PERSON] et al. [17] analyzed the effects of the physicochemical models by solving high temperature chemical nonequilibrium flow, and found that the commonly used chemical kinetic model of [PERSON] generally calculates the larger shock standoff distance than the models of [PERSON] and Park. For complex flow regions such as the shock/shock interaction, the difference between the predicted peak heat flux using different chemical kinetic models is up to 20% or even more. The application of different models results in differences in aerodynamic predictions, which causes confusion in model selection when calculating hypersonic nonequilibrium flow. Above all, previous studies have suggested that a systematic evaluation should be conducted to investigate the combined effects of different thermodynamic and chemical kinetic models commonly used for simulating the hypersonic thermochemical nonequilibrium flow in a comprehensive and detailed way. In this paper, the HyFLOW software [18] is employed to solve the hypersonic thermochemical nonequilibrium flows around a standard cylinder to compare the effects of different thermodynamic models (one- and two-temperature models) respectively with different chemical kinetic models of air (Park 5-species, 7-species, 11-species; Gupta 5-species, 7-species, 11-species; Dunn-Kang 5-species, 7-species, 11-species) on the aerodynamic characteristics, and in the meantime, to investigate whether the reduced models can be used instead of the complex models under certain conditions, for achieving a balance between computational efficiency and computational accuracy. This study firstly summarizes the previous research work and presents the purpose, significance and research methodology of this paper. Secondly, it introduces the mathematical and physical models in detail, including the governing equations, thermochemical nonequilibrium source terms, transport properties, and the HyFLOW software. Then, it shows the hypersonic thermochemical nonequilibrium flow results solved by different model combinations and analyzes the effects of different models on the flow temperature, pressure, shock standoff distance, and wall heat flux. Finally, the conclusions are made.