S-II

S-II
	The Apollo 6 S-II stage during stacking operations in the VAB
Manufacturer	North American
Country of origin	USA
Used on	Saturn V (stage 2); Saturn INT-21 (stage 2);
General characteristics
Height	24.9 m (82 ft)
Diameter	10 m (33 ft)
Gross mass	480,000 kg (1,058,000 lb)
Propellant mass	443,000 kg (977,000 lb)
Empty mass	36,200 kg (79,700 lb)
Launch history
Status	Retired
Total launches	13
Successes; (stage only)	12
Other	Partial failure (Apollo 6)
First flight	November 9, 1967 (AS-501) Apollo 4
Last flight	May 14, 1973 (AS-513) Skylab 1
Rocketdyne J-2
Powered by	5
Maximum thrust	4,400 kN (1,000,000 lbf)
Specific impulse	421 seconds (4.13 km/s)
Burn time	367 s
Propellant	LH2 / 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.