Rocketdyne F-1
The F-1, commonly known as Rocketdyne F-1, is a rocket engine developed by Rocketdyne. This engine uses a gas-generator cycle developed in the United States in the late 1950s and was used in the Saturn V rocket in the 1960s and early 1970s. Five F-1 engines were used in the S-IC first stage of each Saturn V, which served as the main launch vehicle of the Apollo program. The F-1 remains the most powerful single combustion chamber liquid-propellant rocket engine ever developed.
F-1 rocket engine specifications | |
| Country of origin | United States |
|---|---|
| Manufacturer | Rocketdyne |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Mixture ratio | 2.27 (69% O2, 31% RP-1) |
| Cycle | Closed Gas-generator |
| Performance | |
| Thrust, vacuum | 1,746,000 lbf (7,770 kN) |
| Thrust, sea-level | 1,522,000 lbf (6,770 kN) |
| Thrust-to-weight ratio | 94.1 |
| Chamber pressure | 70 bars (1,015 psi; 7 MPa) |
| Specific impulse, vacuum | 304 s (2.98 km/s) |
| Specific impulse, sea-level | 263 s (2.58 km/s) |
| Mass flow |
|
| Burn time | 150-163 s |
| Dimensions | |
| Length | 18.5 feet (5.6 m) |
| Diameter | 12.2 feet (3.7 m) |
| Dry weight | 18,500 lb (8,400 kg) |
| Used in | |
| Saturn V | |
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