A Numerical Study of the Stagnation Point Heat Transfer Rate Characteristics around the Blunt-Body

In this paper the CSCM upwind flux difference splitting method, Viscous Shock Layer method and Fay-Riddell equation have been applied to study the stagnation point heat transfer rate characteristics of the blunt-body in hypersonic flow regime. A numerical experiments have been performed to construct the database of the thermal protection material design by using Mach numbers, wall temperatures, nose radius and nose bluntness. The differences in predicted heat transfer rate among the methods were approximately 10%. The stagnation point heat transfer rates were linearly proportional to wall temperature, the cubic power of free-stream Mach number and inverse square root of nose radius of curvature. The heat transfer rate characteristics around stagnation point would be useful for hypersonic vehicle design.