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.

Supersonic flow characteristics of a dispenser with oponed cabin are numerically simulated with Reynolds-averaged Navier-Stokes equations.Computations are well consistent with experimental results.Flow characteristics are simulated well with S-A turbulent model and splitting scheme AUSM+.If attack angle is not zero,reverse flow is found at backward-facing step of head.Vortices are developed between adjacent submunitions.Several extremes of surface circumferential pressure are shown,and shell tail wave is not symmetric.The principle of flow field is revealed.Vital reference is provided for submunition initial conditions.