Numerical Calculation Aerodynamic Heating Over Projectiles' Head At Hypersonic Flow

The aerodynamic heating and temperature fields of hypersonic projectile's head (Ma=5 ~ 8) in denseness aerosphere were calculated by using the engineering and numerical simulation methods.At the firstly, the Fay-Riddle balance boundary layer stagnation point heat flux formula is applied in computation the stagnation point heat flux of blunt head. Secondly, the heat flux of projectile's head has been unitary expressed by Lees' method. The heat flux formulas have been linearized and expressed as the function of the temperature of projectile's wall in numerical discretization process, and be treated as the boundary conditions of temperature field's numerical simulation.By using the finite volume method (FVM), second-order accuracy, full implicitly format discretizing the three dimensions unsteady state heat conduction equations in unstructured grid. For meeting the grid orthogonality and high precision, calculating the first diffusion (the normal direction) and second diffusion (the tangent direction ) alternately at the same time. The program has been compiled by Fortran95, and realized multifunction of the grid pre-treatment through connected with the commercial software such as Tecplot and Gambit.The engineering method of heat environment and numerical simulation of temperature field are coupling at full validating program's correctness. For simulating the temperature field of two different geometries projectile's head, the tiptop temperature distribution and change rule of dynamic temperature field have been gained.The results indicate that the inlet Mach number and the diameter of projectile's ball head are important factors of aerodynamic heating. The results are rewarding engineer to reference.