Since I have seen someone questioning if the numbers add up.
Saturn V
Individual stage Total vessel
STAGE Total mass Dry mass Total mass Dry mass Isp Delta-v
1 LOX/RP-1 2,300,000 131,000 2,900,000 731,000 263s 3554.2 m/s
2 LOX/LH 480,000 36,000 600,000 156,000 421s 5561.5 m/s
3 LOX/LH 120,800 10,000 120,800 10,000 421s 8796.2 m/s
--------------
17911.9 m/s
Masses are in kg
Does not include delta-v calculations for the lunar lander but assumes the gross vehicle mass of the Saturn V.
Variations of the above are the result of assuming different orbits, launch sites, safety margins and different locations and burn times for maneuvers.
To go from the ground to lunar orbit and return takes around 17,500 delta-v. Which means you need something capable of altering its velocity that much either increasing or decreasing its speed.
The Saturn V assuming it is carrying the maximum payload it can is has 17,900 delta-v. Which leaves a surplus of 400 m/s of acceleration.
The Saturn V was capable of getting to lunar orbit and returning.
Here are the formulas I used:
Here is an explanation for the methodology I used:
http://www.braeunig.us/space/index.htmSo using formulas based on the current understanding of physics it results in telling, at least me, that the Saturn V was capable of carrying men to the moon and back.
I did not calculate the delta-v requirements myself and assumed since multiple sources, including non-government came up with basically the same answer are correct.