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S-II
 | This article needs additional citations for verification. (July 2009) |
 | |
| Manufacturer | North American |
|---|---|
| Country of origin | United States |
| Used on | Saturn V |
| 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.
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