Maybe not quite what you're after, but slide 85 of NASA's Aerothermodynamics Lecture has this figure:

Of course this requires an estimate of instantaneous heat flux along the entry trajectory (integrated into total heat load). A good value for total heat load for a LEO reentry is ~$10^4$ to $2$x$10^4$ $\frac{J}{cm^2}$ which translates to ~10-15% of the entry vehicles mass as TPS (thermal protection system).

This is of course just a 1st (maybe even 0th) order design estimation tool, and specific to ablative entry systems which are generally not reusable.

Maybe not quite what you're after, but slide 85 of NASA's Aerothermodynamics Lecture has this figure:

Of course this requires an estimate of instantaneous heat flux along the entry trajectory (integrated into total heat load). A good value for total heat load for a LEO reentry is ~$10^4$ to $2$x$10^4$ $\frac{J}{cm^2}$ which translates to ~10-15% of the entry vehicles mass as TPS (thermal protection system).

This is of course just a 1st (maybe even 0th) order design estimation tool, and specific to ablative entry systems which are generally not reusable.