Parameters you quote are not too relevant to "performance"
You may quantify performance in terms of $/kg of on-orbit mass, or as %% of takeoff mass delivered to the orbit.
Most launch vehicles would be in a $6-10 /gram range on first number (just to compare - gold is $48/gram as of last Friday. 10 years ago gold was in $10/gram range). Mass-wise, most mid-size launch vehicles are around 3% of mass to orbit; Japanese H-2 being leader at 4.2%; Saturn V is around 4.0%, if my memory serves me right. It's hard to define comparable value for shuttle, since one can argue what should be counted as payload in that case.
Moreover, launch site and destination orbit can change everything. New external tank had to be developed for Shuttle to fly to 51.6 deg. ISS/ Mir orbit. As far as I know, Shuttle would be unable to reach orbit if launched from Russian launch site Bajkonur with empty payload bay.
Next, initial acceleration - is a result of many trade-offs. It can be different even for different rockets in a same family. I remember Boeing's document describing capabilities of Delta rocket with acceleration charts. pretty much every configuration has different acceleration profile.
Basically you do not want to accelerate too much in dense atmosphere, but you don't want to stay there too long. In both cases you loose much needed velocity. Oh, and you want to limit aerodynamic loads and peak acceleration as well, and engines have their limits as well..
Difference between S-5 and Shuttle is in first stage engines - and approach to go through the air. Shuttle use higher thrust, lower specific thrust boosters to kick it out of lower atmosphere, where lower-thrust, higher specific thrust H2
engine can take over.
uses same fuel - H2
- to steadily power it's way through.