Saturn IC C-4B

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Saturn IC C-4B

Part of Saturn IC

LOx/Kerosene propellant rocket stage. Final first stage design of Saturn C-3 (November 1961). Unique S-IC design in that fuel and propellant tank shared common bulkhead; stage was actually shorter than C-3B S-IC.

Status: Study 1961. Thrust: 30,606.40 kN (6,880,592 lbf). Gross mass: 1,450,984 kg (3,198,872 lb). Unfuelled mass: 90,686 kg (199,928 lb). Specific impulse: 304 s. Specific impulse sea level: 265 s. Burn time: 130 s. Height: 33.46 m (109.77 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-4B. Propellants: Lox/Kerosene.

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