To investigate and verify the accuracy，robustness，and computational efficiency of the gas kinetic method in dealing with hypersonic vehicles，numerical simulation is conducted by means of a unified gas kinetics scheme (UGKS) and a gas kinetics inviscid flux (KIF) scheme developed based on the Stanford University Unstructured (SU2) open-source platform (SU2-KIF).The simulation focuses on the steady flow around the HTV-2 typical hypersonic vehicle under the conditions of an incoming Mach number ranging from 6 to 12，a flight altitude ranging from 30 km to 70 km，and a flight angle of attack ranging from 5° to 20°.The distributions of heat flow and pressure on the vehicle surface，as well as the aerodynamic force and moment coefficients，are statistically analyzed，and the changes in the aerodynamic force and aerothermal effects during the flight process are investigated.