H-1 (rocket engine)
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![A cluster of 8 H-1 rocket engines lifted the Saturn I from the launch pad. [(See the original diagram with specifications.)]](http://en.wikipedia.org/wiki/Image:H-1_rocket_engine.jpg "A cluster of 8 H-1 rocket engines lifted the Saturn I from the launch pad. [(See the original diagram with specifications.)]")
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 use in the S-IB first stage of the Saturn I and Saturn IB rockets. It is used in clusters of eight 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
| 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 | 289 s | 289 s |
| 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) | |
| Oxidizer flow rate | 3330 USgal/min (210 L/s) | |
| Nominal chamber pressure | 633 psia (4.4 MPa) | |
- 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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