So I was looking into the payload mass a fully fuelled Centaur V could send to Jupiter and used the formula in presented in this answer to create a C3 graph. For a bit of fun I also looked into the payload capacity of Starship and was surprised to find out that it had 0kg capacity to that orbit; it reaches 0 at 63.37 $km^2/s^2$, well short of the ~82 $km^2/s^2$. The graph is based on the C3 graph presented here. Is my working out incorrect or does a fully fuelled Starship seriously not have the ability to send a payload to Jupiter? This is somewhat pertinent given questions like this.
On a side note, I also did delta-v calculations for it and found that it has plenty of payload to Jupiter; 86 tons. Are the delta-v assumptions from this graphic too optimistic or can delta-v not be used to predict payload mass or is this graph correct and the C3 graph incorrect?
edit: So I also looked into the EUS deep space capabilities and this one confuse me. The engineering parameters come from this document. The lunar payload of the EUS here has greater capacity then what is shown in this C3 graph, which makes sense because EUS when riding on SLS B1B is deployed on a suborbital trajectory and would lose some performance. However once we get to Jupiter it ends up being 2.83 tons, well short of the 8 tons of SLS B1B, which doesn't make sense given that it's performance should be boosted. Is this method of calculating C3 performance just inaccurate? (@uhoh help please)