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The H-1 engine is a 200,000 lbf (890 kN) thrust LOX/RP-1 engine, used alone in the first stages of some Thor - Delta rockets and the Jupiter rocket. It is derived from the Navaho missile, and was simplified and improved for S-IB use. It is used in clusters on all S-IB rocket stages. Later it would be uprated to 205,000 lbf (912 kN) of thrust. The H-1 preceded the F-1 engine, which was used on the Saturn V rocket.
Specifications
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Vehicle Effectivity |
| SA-201 through SA-205 |
SA-206 and subsequent |
| Thrust (sea level) |
200,000 lbf (890 kN) |
205,000 lbf (912 kN) |
| Thrust duration |
155 s |
155 s |
| Specific impulse |
260.5 lbf.min/lb (153 kNs/kg) |
261.0 lbf.min/lb (154 kNs/kg)</ |
| Engine weight dry (inboard) |
1,830 lb (830 kg) |
2,200 lb (998 kg) |
| Engine weight dry (outboard) |
2,100 lb (953 kg) |
2,100 lb (953 kg) |
| Engine weight burnout |
2,200 lb (998 kg) |
2,200 lb (998 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) |
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| Oxidizer flow rate |
3330 USgal/min (210 L/s) |
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| Nominal chamber pressure |
633 psia (4.4 MPa) |
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- Contractor: NAA/Rocketdyne
- Vehicle Application: Saturn I / S-IB 1st stage - 8-engines
- Vehicle Application: Saturn IB / S-IB 1st stage - 8-engines
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