Abstract: High enthalpy shock tunnel flow field is different from that of flight condition, and accurate simulation of chemical reaction aeroheating at stagnation point is very important for hypersonic vehicle. Based on equilibrium boundary layer and frozen boundary layer stagnation heating formula, the effects of the dissociation enthalpy were analyzed on the aeroheating on stagnation point with different catalycity characteristics. We also analyzed the differences between the ground wind tunnel experiments and flight data with respect to the variation in non-equilibrium flow head after head shock wave, the influence of surface catalytic characteristics of the flow field parameters. The simulation criteria are propsed for establishment of a ground high enthalpy wind tunnel simulation of fully catalytic wall stagnation aerodynamic heating. As long as the simulation is valid for the stagnation pressure, stagnation velocity gradient, flow enthalpy in wind tunnel conditions, the sky flight state aerodynamic heating is reproducible. According to different tests carried out with different size models, numerical simulation is verified for chemical non-equilibrium flow field. The results show that the ground wind tunnel simulation cannot simulate the parameters of the flow field near the stagnation zone. The catalytic properties of materials have great impact on the flow field near the wall with N and O elements. The aeroheating at stagnation point of complete catalysis wall from ground 1:1 simulation is lower than that from the flight data, while the flight status of the stagnation zone regarding the enthalpy, the pressure, and the heat flux can be reproduced according to the model size detemined by three parameters simulation criterion. With head radius increasing, the simulation and flight data tend to be identical with respect to the wall temperature and the gradients of the N and O components near the stagnation line.