MSFC study, 1965. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 6 F-1 engines; S-II stretched 156 inches with 1.2 million pounds propellant and 7 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.

LEO Payload: 145,000 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 54,400 kg. to a: Translunar trajectory. Liftoff Thrust: 4,128,330 kgf. Total Mass: 3,648,700 kg. Core Diameter: 10.1 m. Total Length: 121.0 m.

• Stage Number: 1. 1 x Saturn MS-IC-1A Gross Mass: 2,694,700 kg. Empty Mass: 160,600 kg. Thrust (vac): 4,735,900 kgf. Isp: 304 sec. Burn time: 160 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 48.2 m. Propellants: Lox/Kerosene No Engines: 6. F-1

• Stage Number: 2. 1 x Saturn MS-II-1A Gross Mass: 600,800 kg. Empty Mass: 60,000 kg. Thrust (vac): 650,675 kgf. Isp: 421 sec. Burn time: 345 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 29.6 m. Propellants: Lox/LH2 No Engines: 7. J-2

• Stage Number: 3. 1 x Saturn MS-IVB-1A Gross Mass: 179,200 kg. Empty Mass: 20,400 kg. Thrust (vac): 105,200 kgf. Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 22.8 m. Propellants: Lox/LH2 No Engines: 1. J-2

• 228 - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. HTML when accessed: http://www.webcreations.com/ptm
• 230 - Saturn V Improvement Study, Final report, NASA Contract NAS8-11359.