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![]() F-1 engine on display at Kennedy Space Center | |
Country of origin | ![]() |
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First flight | November 9, 1967Apollo 4) | (
Last flight | May 14, 1973Skylab 1) | (
Designer | Rocketdyne |
Manufacturer | Rocketdyne |
Associated LV | Saturn V, Saturn C-3, Saturn C-4, Saturn C-8 |
Liquid-fuel engine | |
Propellant | LOX / RP-1 |
Mixture ratio | 2.27:1 (69% LOX, 31% RP-1) |
Cycle | Gas-generator |
Performance | |
Thrust, vacuum | 7,770 kN (1,746,000 lbf) |
Thrust, sea-level | 6,770 kN (1,522,000 lbf) |
Thrust-to-weight ratio | 94.1:1 |
Chamber pressure | 70 bar (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 to 163 seconds |
Dimensions | |
Length | 5.6 m (18.5 ft) |
Diameter | 3.7 m (12.2 ft) |
Dry mass | 8,400 kg (18,500 lb) |
Used in | |
S-IC |
The F-1 is a rocket engine developed by Rocketdyne. The 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.[1]
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