A method with CFD technology is used for accurate prediction of temperature field of supersonic and hypersonic kinetic energy projectiles.It includes equilibrium flow governing equations and difference scheme,equilibrium flow Jacobian matrixs and equilibrium gas state equations.A real gas equilibrium air model is used to calculate temperature in vector flux split in a difference scheme.Thermal environment for typical high-speed kinetic energy projectile is validated.Rationality of the method is considered.Temperature field of a designed hypersonic kinetic energy projectile is simulated.Reliable numerical data for projectile aerodynamic design and aerodynamic heat protection are provided.