S-II

S-II
The Apollo 6 S-II stage during stacking operations in the VAB
ManufacturerNorth American
Country of originUnited States
Used onSaturn V
General characteristics
Height24.9 m (82 ft)
Diameter10 m (33 ft)
Gross mass480,000 kg (1,058,000 lb)
Propellant mass443,000 kg (977,000 lb)
Empty mass36,200 kg (79,700 lb)
Launch history
StatusRetired
Total launches13
Successes
(stage only)
12
OtherPartial failure (Apollo 6)
First flightNovember 9, 1967 (AS-501) Apollo 4
Last flightMay 14, 1973 (AS-513) Skylab 1
Rocketdyne J-2
Powered by5
Maximum thrust4,400 kN (1,000,000 lbf)
Specific impulse421 seconds (4.13 km/s)
Burn time367 s
PropellantLH2 / LOX

The S-II (pronounced "S-two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.