Specifications
- Contractor: NAA/Rocketdyne
- Vehicle Application: Saturn I / S-I 1st stage - 8 engines
- Vehicle Application: Saturn IB / S-IB 1st stage - 8 engines
| Vehicle effectivity | ||
|---|---|---|
| SA-201 through SA-205 | SA-206 and subsequent | |
| Thrust (sea level) | 200,000 lbf (890 kN) | 205,000 lbf (910 kN) |
| Thrust duration | 155 s | 155 s |
| Specific impulse | 289 s | 289 s |
| Engine weight dry (inboard) | 1,830 pounds (830 kg) | 2,200 pounds (1,000 kg) |
| Engine weight dry (outboard) | 2,100 pounds (950 kg) | 2,100 pounds (950 kg) |
| Engine weight burnout | 2,200 pounds (1,000 kg) | 2,200 pounds (1,000 kg) |
| Exit-to-throat area ratio | 8:1 | 8:1 |
| Propellants | LOX & RP-1 | LOX & RP-1 |
| Mixture ratio | 2.23±2% | 2.23±2% |
| Fuel flow rate | 2092 USgal/min (132 L/s) | |
| Oxidizer flow rate | 3330 USgal/min (210 L/s) | |
| Nominal chamber pressure | 633 psi (4.36 MPa) | |
Read more about this topic: H-1 (rocket Engine)