Image:H-1 rocket engine.jpg
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The H-1 rocket engine stands 8.8 feet (268 cm) high and 4.9 feet (149 cm) wide. It was used for the Saturn I and Saturn IB rocket systems.
|   | Vehicle Effectivity | |
|---|---|---|
| SA-201 through SA-205 | SA-206 and subsequent | |
| Thrust (sea level) | 200,000 lb (890 kN) | 205,000 lb (912 kN) |
| Thrust duration | 155 sec | 155 sec |
| Specific impulse (lb-sec/lb) | 260.5 min | 261.0 min |
| 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% |
- Contractor: NAA/Rocketdyne
- Vehicle application: Saturn IB/S-IB stage (eight engines)
[edit] See also
[edit] Provenance
Image downloaded from NASA Marshall Spaceflight Center Image (MIX) Exchange server:
http://mix.msfc.nasa.gov/ABSTRACTS/MSFC-9801768.html
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- (del) (cur) 02:57, 9 July 2004 . . Ke4roh (Talk | contribs) . . 439×623 (40,744 bytes) (crop to just the engine)
- (del) (rev) 01:27, 10 June 2004 . . Reubenbarton (Talk | contribs) . . 640×480 (97,083 bytes) (H-1 Saturn I and Saturn IB rocket engine)
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