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F-1

Engine · USA

Original archive entry. The text, images and links below are kept as they were written.

F-1 engine
F-1 engine
Credit: © Mark Wade

Rocketdyne LOx/Kerosene rocket engine. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967.

Used in Saturn IC. The largest liquid engine rocket motor ever developed, it represented an incredible order-of-magnitude development from the 150,000 lb thrust class motor developed for Navaho, Jupiter, Thor, Atlas, Titan I, and Saturn I. Severe combustion stability problems were solved during development and it never failed in flight. Proposed for use on Nova NASA-1; Nova A-1; Nova NASA-2; Jarvis-1; Nova B-1; Nova 59-4-2; Saturn MLV 5-23L-0; Saturn S-IB-2; Nova 59-4-1; Nova 60-8-1; Saturn S-ID; Saturn S-IB-4. Saturn V S-1C Stage. Designed for booster applications. Gas generator, pump-fed.

Thrust (sl): 6,747.500 kN (1,516,898 lbf). Thrust (sl): 688,062 kgf. Engine: 8,391 kg (18,498 lb). Chamber Pressure: 70.00 bar. Area Ratio: 16. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 94.0680252651651. Oxidizer to Fuel Ratio: 2.27. Coefficient of Thrust vacuum: 1.815664036964. Coefficient of Thrust sea level: 1.58709260839257.

Subtopics

  • F-1A Rocketdyne LOx/Kerosene rocket engine design of 1968. Improved version of the F-1, which would have been used in any follow-on production of Saturn launch vehicles. Designed for booster applications. Gas generator, pump-fed.
Country
USA
Propellants
Lox/Kerosene
Bibliography
225