Spacecraft Heat-shield ABLATION
 

I wanted to simulate ablation for heat shield of a spacecraft while orbital re-entry. Can someone provide me with an overview and/or specific steps I need to do to simulate the above mentioned problem?

Thanks in advance :)

If you still need some sources, take a look here:
http://padis.uniroma1.it/bitstream/1...9E07C7D2A5B53A

I'm also interested in ablation phenomena (no space travel though), do you happen to know if a mass source term in the density continuity equation and an energy term are enough, or is there also an impulse term needed?

I've seen works which used an impulse term, and some that didn't. I expect that the gas flow created by the ablation process has a significant impact on my result, so this is critical for me.