ABOUT F-1
The F-1 is the most powerful single-chamber liquid-fueled rocket engine ever flown, developed by Rocketdyne for the Saturn V first stage during the Apollo program. Five F-1 engines generated 33,000 kN of thrust to lift the Saturn V off the pad. Its gas generator cycle design and massive scale remain an engineering marvel, and no single-chamber engine has since matched its thrust.
Image: NASA
PERFORMANCE
| Thrust (Sea Level) | 6,770 kN (1,522,000 lbf) kN |
| Thrust (Vacuum) | 7,740 kN (1,740,100 lbf) kN |
| ISP (Sea Level) | 263 s s |
| ISP (Vacuum) | 304 s s |
| Chamber Pressure | 7.0 MPa (1,015 psi) bar |
| Mass | 8 kg |
| Thrust-to-Weight | 94 |
| Throttle Range | Not throttleable |
| Restart Capable | No |
THRUST CONVERSIONS (VACUUM)
| Kilonewtons | 7.0 kN |
| Pounds-force | 1,574 lbf |
ENGINE CYCLE
Gas Generator
A gas generator cycle taps off a small portion of propellants to drive turbopumps via a separate combustion chamber. The turbine exhaust is dumped overboard, making it less efficient but simpler and more reliable. Used by the Merlin, F-1, and RS-27.
PROPULSION
| Propellant | RP-1 |
| Oxidizer | LOX |
| Engine Cycle | Gas Generator |
| Mixture Ratio | 2.27:1 |
| Flow Rate | ~2,578 kg/s kg/s |
PHYSICAL
| Dimensions | 3.76 m diameter × 5.79 m length |
| Combustion Chambers | 1 |
| Nozzle Expansion Ratio | 16:1:1 |
GENERAL
| Manufacturer | Rocketdyne |
| Country | United States |
| Status | Retired |
| First Flight | April 17, 1967 |
VARIANTS (2)
- F-1
- F-1A (uprated, never flown)
VEHICLES USING F-1 (1)
- Saturn V (S-IC stage)
ENGINE LINEAGE
F-1→F-1B (proposed upgrade)
⚖ PROPELLANTS
