Evaluation of Thermodynamic and Chemical Kinetic Models for Hypersonic and High-Temperature Flow Simulation  
[PERSON]  
1 School of Energy and Power Engineering, Shandong University, Jinan 250061, China; [EMAIL_ADDRESS] (W.Z. ); [EMAIL_ADDRESS] (C.X. )1 School of Aeronautic Science and Engineering, Beihang University (BUAA), Beijing 100191, China; 1 [EMAIL_ADDRESS]  
[PERSON]  
1 School of Energy and Power Engineering, Shandong University, Jinan 250061, China; [EMAIL_ADDRESS] (W.Z. ); [EMAIL_ADDRESS] (C.X. )1 School of Aeronautic Science and Engineering, Beihang University (BUAA), Beijing 100191, China; 1 [EMAIL_ADDRESS]  
[PERSON]  
1 School of Energy and Power Engineering, Shandong University, Jinan 250061, China; [EMAIL_ADDRESS] (W.Z. ); [EMAIL_ADDRESS] (C.X. )1 School of Aeronautic Science and Engineering, Beihang University (BUAA), Beijing 100191, China; 1 [EMAIL_ADDRESS]  
[PERSON]  
2 China Aerodynamics Research and Development Center, Mianyang 621000, China [EMAIL_ADDRESS] (W.Z. )[EMAIL_ADDRESS] (C.  
its reentry from orbit in 2003 [2], leading to the recognition that the study of aerodynamic heating is a critical problem that cannot be bypassed on the road of hypersonic flight. When the hypersonic vehicle flies at very high speed in atmosphere, a strong bow shock wave forms around the blunt nose of the vehicle due to the sharp compression of air. The flow temperature behind the shock can exceed thousands or even 10,000 K, resulting in the severe aerodynamic heating to the vehicle as well as the excitations of internal energy modes, dissociation and ionization reactions of air species. The air ionization generates the plasma to intervene with the electromagnetic wave transmission, which leads to the communication signal interruption, that is \"blackout\" [5]. In fact, the excitation of internal energy modes and chemical reactions of air species do not occur independently and are always intercoupling. For example, the molecules in the high vibrational level prefer to dissociate, while the dissociation reaction leads to the loss of total vibrational energy [6]. In the meantime, when the characteristic times of the relaxations of internal energy excitation or chemical reactions reach comparable level to the characteristic time of flow, there are thermochemical nonequilibrium effects, which can greatly affect the aerothermodynamic environment of the hypersonic vehicle. Therefore, it is very important to predict the thermochemical nonequilibrium processes accurately for the design of hypersonic vehicle [7]. However, limited to the operation cost and technical conditions, it is still very difficult to reproduce the high-temperature and high-enthalpy environment of real hypersonic flight on the ground. Therefore, numerical simulation becomes an indispensable technique for evaluating the aerothermodynamic properties of the hypersonic flow. Until now, many different thermodynamic and chemical kinetic models have been developed by [PERSON] [8,9], [PERSON] et al. [10], [PERSON] and [PERSON] [11] to calculate the thermochemical nonequilibrium effects in the hypersonic flow, which have become the foundations of the related numerical studies over decades. [PERSON] et al. [12] investigated the hypersonic shock wave/turbulent boundary layer interaction with the thermochemical nonequilibrium effects using the [PERSON]'s two-temperature model and [PERSON] 11-species model. The results showed that the combined effect of turbulence and thermochemical nonequilibrium has a significant impact on the flow structure, wall characteristic and separation length of the shock/boundary layer interaction. By comparing the effects of [PERSON], [PERSON], Park 87 and Park 91 chemical kinetic models on the hypersonic aerodynamic heating, [PERSON] et al. [13] found that the heat flux on the surface of a vehicle with the complex shape is more sensitive to the choice of chemical reaction model, and the maximum difference of the peak heat flux may exceed 25%. [PERSON] et al.