Aerobraking is a benefit but is the Dragon really unable to land on the moon? The moon has less gravity (about half) and the velocity difference should be much smaller for a lunar intercept than a Mars intercept.

Has anyone got numbers for this?

Dragon doesn't have enough delta-V to land on the moon. The plan for a Mars landing is to use it as a lifting body to keep it above the ground for long enough to shed most of its velocity.

I've read various statements which say that Dragon can land on the Moon, such as http://www.nbcnews.com/science/space/mars-ahead-spacex-unvei... :

> Musk has said a fully loaded Dragon could even be sent to make a touchdown on the moon or Mars

or https://www.nasaspaceflight.com/2016/04/spacex-debut-red-dra... :

> “With Dragon launched on a Falcon Heavy, it can go pretty much anywhere in the solar system, because that’s a heck of a big rocket,” he continued.

> “Dragon, with the heat shield, parachutes and propulsive landing capability, is able to land on a planet that has higher entry heating, like Mars. It can also land on the Moon, or potentially conduct a Europa mission.”

How does that fit with the statement "Dragon doesn't have enough delta-V to land on the moon"?

Yes, GP said that already but I'm after the numbers here. How much delta-v the Dragon has? And what are the approximate requirements for Moon vs. Mars landing?

The Dragon 2 has about 1.6 km/s. Apollo had 2.47 km/s to land and 2.22 km/s to take off. Oh, and it would take on the order of 4.5 km/s to take off from Mars and maybe a few hundred to land.

Thanks! These numbers look reasonable to me. Can you provide a link to source (s)? I'd like to read some more...