I've seen lots of flight profiles that give Max Q during ascent. Around 33 to 35 kilopascals, if memory serves. But I have been having a hard time finding Max Q during descent.
With the recent reuse of a SpaceX booster there has been some talk of also reusing an upper stage. The re-entry dynamic pressure and temperature seem to me to be the major obstacles barring re-use. But I don't really know the Max Q of an upper stage re-entering the atmosphere. Given that an upper stage will have a delta V budget of around 6 or 7 km/s, the dry mass fraction is less than that of a re-entering capsule. If the dry mass fraction is 5%, it would be difficult to give the re-entering stage robust structure and thermal protection.