More nerdy calculations

I wanted to see what kind of mass you can get off the Martian surface and the lunar surface with a full tank on the surface to low orbit.

This chart may be hard to read. There's three columns of the rocket equation with parameters, reading down top to bottom. The last row are the delta-vees. Destinations/arrivals are on top two rows.

The middle column is Mars low orbit to Lunar Lagrange point two. Maxxed out Starship version 3 ships are 2300 tons. That means we aren't maxxed out here except for the first column. If it was maxxed out, the wet mass minus the dry mass would be 2300 tons, but obviously isn't for the middle column and right column. I've already forgotten why that is, so it isn't necessarily a mistake. But could be. Too white and nerdy, eh?

You might notice that this is one helluva lot of mass to lift off these places. Or land on these places for that matter. That's the point. On Earth, the numbers are much smaller. This is an opportunity, I would think.

______________Mars____MLOrbit_________Lunar Launch/landing

_____________ MLO_____OPT-Eml2_________Luna-EML2

wet mass ton 3600_________3650_________4600

dry mass ton 1300_________1650_________2300

isp _________ 380_________ 380_________ 380

grav const___9.81_________9.81 ________9.81

delta v m/s__3797_________2959 _______ 2521