 S-V stage on top of the S-IV | |
| Manufacturer | Convair |
|---|---|
| Country of origin | United States |
| Used on | Saturn I (stage 3) |
| General characteristics | |
| Height | 9.14 m (30.0 ft) |
| Diameter | 3.05 m (10.0 ft) |
| Gross mass | 15,600 kg (34,400 lb) |
| Propellant mass | 13,604 kg (30,000 lb) |
| Empty mass | 1,996 kg (4,400 lb) |
| Associated stages | |
| Family | Saturn |
| Derivatives | Centaur |
| Launch history | |
| Status | Retired |
| Total launches | 4 |
| Successes (stage only) | 4 |
| Failed | 0 |
| First flight | October 27, 1961 |
| Last flight | March 28, 1963 |
| S-V | |
| Powered by | 2 RL-10 engines |
| Maximum thrust | 133.45 kN (30,000 lbf) |
| Specific impulse | 425 s (4.17 km/s) |
| Burn time | 425 s |
| Propellant | LH2 / LOX |
The S-V (pronounced "S-five") was the third stage of the Saturn I rocket. It was built by Convair. It was designed to use two RL-10A-1 engines fueled by liquid hydrogen (LH2) and liquid oxygen (LOX) in tanks utilizing a common bulkhead to separate the propellants.