S-1C details Credit - © Mark Wade

MSFC study, 1968. Essentially identical to Saturn INT-20; standard Saturn IC stage together with Saturn IVB second stage, with Centaur third stage for deep space missions.

Manufacturer: Von Braun. LEO Payload: 60,000 kg (132,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 18,200 kg (40,100 lb). to a: Translunar trajectory. Liftoff Thrust: 33,737.900 kN (7,584,582 lbf). Total Mass: 2,478,120 kg (5,463,310 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 72.00 m (236.00 ft). Flyaway Unit Cost $: 391.500 million. in: 1985 unit dollars.

• Stage Number: 1. 1 x Stage: Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1.

• Stage Number: 3. 1 x Stage: Saturn IVB (S-V). Gross Mass: 119,900 kg (264,300 lb). Empty Mass: 13,300 kg (29,300 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Saturn V version of S-IVB stage

• Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.