Study Of Flow Field Characteristics For Hypersonic Calorically Perfect Gas

As aerothermal makes great effect on the design of aircrafts, predicting thermal environment of aircrafts accurately becomes more and more popular. In this paper, we research numerical simulation in hypersonic aerothermal by computational fluid dynamics, establish the numerical simulation method in the model of calorically perfect gas and write the corresponding computer program to calculate the aerothermal.Firstly, control equations are established on the basis of flow field characteristics in hypersonic calorically perfect gas, which named Navier-Stokes equations, including mass conservation equation, momentum conservation equation and energy conservation equation. Secondly, the control equations are transformed to the dimensionless form to eliminate the impact of different system of units. Carry on the modeling to flow field, generate two and three dimensional body fitted grid, and transform the dimensionless control equations in Cartesian coordinate system into the ones in body fitted grid coordinate system. Meanwhile, initial conditions and boundary conditions are determined. Thirdly, the numerical discrete equations of this model are established by using four finite difference schemes(including S-W(FVS), V-L(FVS), AUSM+ and AUSMPW) in spatial discretization of inviscid items, central difference in spatial discretization of viscous terms, and upwind scheme in time discretization of conserved variables.With these methods, the code is written to calculate various physical parameters in flow field of hypersonic calorically perfect gas aerothermal. Comparison results with literature, verify the correctness of the program and discover the general laws of the flow field. And talk over the changes of the respective physical parameters under different conditions in the actual high-altitude environment, which establishes calculation methods for solving the flow field.