Rocketdyne F-1

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F-1

F-1 engine on display at Kennedy Space Center
Country of origin	United States
First flight	November 9, 1967 (1967-11-09) (Apollo 4)
Last flight	May 14, 1973 (1973-05-14) (Skylab 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	LOX: 1,789 kg/s (3,945 lb/s) RP-1: 788 kg/s (1,738 lb/s)
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]