I'm looking for some estimates of Dragon's ballistic or drag coefficients in its reentry (heat shield forward) configuration. Estimates for other spacecraft would be useful also as they would give me some intuition of what's normal and what's not. I know the exact numbers depend on many factors like air density, velocity, etc, but it's OK if you know them for just some (any) particular configuration. Ballpark figures OK. Thanks!
This may be of help to you: Planetary Mission Entry Vehicles Quick Reference Guide. Version 3.0. It contains lots of data on various entry probes (including ballistic coefficients) although it only goes up until 2003 (MER-A & MER-B).
Not knowing how much you already know about this, I'll just point out that drag coefficients at high speeds (10-25 Ma) are still Mach number dependent, though far less so than at low Mach number (less than 3 Ma). They are also dependent on air density and pressure (Reynolds effect). Most modeling takes a simplified approach and ignores much of this. Suggest looking at John Anderson's book on introduction to flight or fundamental aerodynamics to see some graphs of coefficient of drag vs Mach that make this point. The topic you ask about is referred to as "blunt body" aerodynamics.