I'm primarily looking for comparison of currently operational orbital launch vehicles by system-specific impulse, or Issp, and to get a fair impression of achievable rocket propellant performance and not merely theoretical maximum sea-level and vacuum specific impulse of propellants, or Isp, per weight. For the sake of having some direct quotes also in answers, please provide the following information:
- Highest Issp achieved by a complete launch vehicle configuration, and
- Highest Issp achieved by a single rocket stage.
For completeness, please also quote most relevant technical information about them, e.g. total impulse delivered by the mass of contained propellant, total (wet) mass of the propulsion system, propellants used, etc. To keep the length of answers manageable, we shall limit ourselves to only the highest performing launch vehicles and stages, but if you can also provide links to any such external launch vehicle and rocket stage comparisons by Issp that is more complete, then even better.
Edit to add: Some related lists that might help you answer my question:
- Wikipedia on Comparison of orbital rocket engines
- Wikipedia on Comparison of orbital launch systems
- Wikipedia on Comparison of orbital launchers families
Kudos to @PearsonArtPhoto for the first link that also enables sorting of rocket engines by their thrust-to-weight ratio, which is essentially what this question is about and that does nearly all the work to answer the second part of my question. As same rocket engines might be used on different launch systems and their stage configurations, some additional work would have to be done, but it is an excellent start.