Saturn IC C-5A

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Saturn IC C-5A

Part of Saturn IC

LOx/Kerosene propellant rocket stage. Final first stage design of Saturn C-5 (November 1961) before selection as Apollo launch vehicle and development in Saturn V.

Status: Study 1961. Thrust: 38,257.99 kN (8,600,738 lbf). Gross mass: 2,217,285 kg (4,888,276 lb). Unfuelled mass: 131,495 kg (289,896 lb). Specific impulse: 304 s. Specific impulse sea level: 265 s. Burn time: 160 s. Height: 42.87 m (140.64 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-5, Saturn C-5N. Propellants: Lox/Kerosene.

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