[cfmyd]

Hi everyone,

I'm running simulations of a sphere in hypersonic flow. I'm getting great results for pressure coefficient along the walls and the total drag, and you can see from the Mach number contours that the shock profile looks correct.
MachNum.jpg

The heat transfer to the walls, however, is not. For some reason the heat transfer at the stagnation point (at the "axis" boundary condition) is not the largest value, and when I refined the mesh I found it would consistently approach 0.
SurfaceHeatFlux.jpg

I've tried everything I can think of so far: refining and coarsening the mesh, decreasing y+ along the wall, steady and transient solutions, different turbulence models, and different wall temperatures, and in all cases this stagnation point discrepancy comes up. If anybody has any ideas on how to correct this, please let me know.

I can give out more info if need be. Thanks!