Saturn IC C-3B

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Saturn IC C-3B

Part of Saturn IC

LOx/Kerosene propellant rocket stage. Final first stage design of Saturn C-3 (November 1961).

Status: Study 1961. Thrust: 22,954.80 kN (5,160,444 lbf). Gross mass: 1,160,787 kg (2,559,097 lb). Unfuelled mass: 72,549 kg (159,943 lb). Specific impulse: 304 s. Specific impulse sea level: 265 s. Burn time: 140 s. Height: 34.41 m (112.89 ft). Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft).

No Engines: 5.

Country: USA. Engines: F-1. Launch Vehicles: Saturn C-3B, Saturn C-3BN. Propellants: Lox/Kerosene.

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