It would be nice to get an overview of what the launchers are capable of in terms of actual space missions. I understand that this depends on many factors, but the Hohmann trajectory seems to be a common and major factor for many missions. Could this Hohmann part of the puzzle be summarized in a table with payload mass for different launchers and destinations?
Most interesting would be to compare these three launcher classes:
SLS or Saturn V
Atlas V551 or Ariane 5 or Proton
The smaller Falcon 9, Soyuz, Indian PSLV would also be of interest since even little PSLV actually has launched an orbiter to Mars.
Latitude of the launch site should not make a difference big enough to matter for an overview purpose, one could assume the equator. The eccentricity and inclination of the destination object is much more important and variable over time. But except for Mars and Mercury, I would think that at least the planets have low enough eccentricity for an average to work well.
Gravity assists, Oberth effect, continuous ion thrusting of course totally distorts the Hohmann geometry and all spacecraft to outer planets have and surely will use Jupiter for gravity assist. So that kind of leaves only Jupiter and Venus and the Moon! But those are very likely mission targets. Each launcher should have a pretty good specification as an X tons to Venus or Y tons to Jupiter or Z tons to the Moon vehicle. For Mars and asteroids the specific launch date seems to be too important. However, Mars will make a close opposition in 2035 which could be used as a benchmark for a crewed mission.