F-1

Also known as Rocketdyne F-1, Rocketdyne F1

rocket engine by Rocketdyne

Key facts

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 launch vehicle span lv: Saturn V , Saturn C-3 , Saturn C-4 , Saturn C-8
Propellant: LOX / RP-1
Mixture ratio: 2.27:1, (69% LOX, 31% RP-1)
Cycle: Gas-generator
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
Length: 5.6 m (18.5 ft)

via Wikipedia infobox

Wikidata facts

Diameter: 3.76
Mass: 8391
Image: F-1 rocket engine at KSC.jpg
Height: 5.79

Show 3 more facts

Commons category: F-1 (rocket engine)
specific impulse by weight: 263
maximum thrust: 1522000

Sources (3)

via Wikidata · CC0

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Article

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.

History