F-1A
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: Boeing / Rocketdyne
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.
Thrust (sl): 8,003.800 kN (1,799,326 lbf). Thrust (sl): 816,178 kgf. Engine: 8,098 kg (17,853 lb). Chamber Pressure: 70.00 bar. Area Ratio: 16. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 115.71.
Related
- Country
- USA
- Launch Vehicles
- Nova GD-B, Nova MM 1B, Nova MM 1C, Saturn MLV-V-1, Saturn MLV-V-2, Saturn MLV-V-3, Saturn MLV-V-1/J-2T/200K, Saturn MLV-V-1/J-2T/250K, Saturn V-24(L), Saturn MLV-V-4(S)-B, Saturn V-25(S)B, Saturn V-3B, Saturn V-4X(U), Saturn V-25(S)U
- Propellants
- Lox/Kerosene
- Agency
- Rocketdyne
Photo Gallery
Advanced Engines
Advanced Engines planned for uprated Saturn and Nova boosters
Credit: © Mark Wade
