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S-I stage
LOx/Kerosene propellant rocket stage. Configuration as flown, Saturn I.

AKA: Saturn I. Status: Flown 1961. Thrust: 7,582.10 kN (1,704,524 lbf). Gross mass: 432,681 kg (953,898 lb). Unfuelled mass: 45,267 kg (99,796 lb). Specific impulse: 289 s. Specific impulse sea level: 255 s. Burn time: 150 s. Height: 24.48 m (80.31 ft). Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft).

Cost $ : 43.500 million. No Engines: 8.

Subtopics
Super-Jupiter stage LOx/Kerosene propellant rocket stage. Earliest member of what would become the Saturn family. Masses estimated.
Jupiter Cluster LOx/Kerosene propellant rocket stage. Masses estimated (cluster of four Jupiter IRBM stages).
Saturn S-IB-2 LOx/Kerosene propellant rocket stage. .
Saturn S-IB-4 LOx/Kerosene propellant rocket stage. .
Saturn IB stage LOx/Kerosene propellant rocket stage. Configuration as flown, Saturn IB.
Saturn S-IB-A LOx/Kerosene propellant rocket stage. Douglas Studies, 1965: S-1B with 225 k lbf H-1's.
Saturn IB-11 LOx/Kerosene propellant rocket stage. 20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units.
Saturn IB-15 LOx/Kerosene propellant rocket stage. 10 foot stretch of Saturn IB. Not found useful in any configuration except with Minuteman first-stage strap-ons to augment thrust.
Saturn S-1B-4 LOx/Kerosene propellant rocket stage. Chrysler Studies, 1966: S-1B with 4 H-1's for use with Titan UA1205 strap-ons.
Country: USA. Engines: H-1 engine. Launch Vehicles: Juno V-A, Juno V-B, Saturn A-1, Saturn C-2, Saturn C-1, Saturn I Blk2, Saturn I. Propellants: Lox/Kerosene.
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