Rocketdyne F-1

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F-1

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	Gas-generator (Open Cycle)
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	3,945 lb/s (1,789 kg/s) (LOX) 1,738 lb/s (788 kg/s) (RP-1)
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

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.^[1]