During launcher ascent, dynamic pressure evolution is described in this answer for the Saturn V. I suppose this is similar for most launchers.
Given the protections designed for reentry, I suppose dynamic pressure involved during reentry is more important than that during ascent.
What does this evolution look like during reentry? Does it look like the same bell shaped curve (which increases and decreases with almost the same slope)?
In case the answer varies with the spacecraft in consideration, this question can be narrowed to vehicles from the Apollo program or other manned ships.