S-1C details Credit: © Mark Wade. 40,371 bytes. 510 x 391 pixels.

MSFC study, 1965. Saturn V core, strengthened but not stretched, with 4 Titan UA1205 strap-on solid rocket boosters.

LEO Payload: 118,000 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 52,900 kg. to a: Translunar trajectory. Liftoff Thrust: 5,599,410 kgf. Total Mass: 3,947,350 kg. Core Diameter: 10.1 m. Total Length: 102.0 m. Flyaway Unit Cost $: 463.42 million. in 1985 unit dollars.

• Stage Number: 0. 4 x Titan UA1205 Gross Mass: 226,233 kg. Empty Mass: 33,798 kg. Thrust (vac): 596,474 kgf. Isp: 263 sec. Burn time: 115 sec. Isp(sl): 238 sec. Diameter: 3.1 m. Span: 3.1 m. Length: 25.9 m. Propellants: Solid No Engines: 1. UA1205

• Stage Number: 1. 1 x Saturn IC Gross Mass: 2,286,217 kg. Empty Mass: 135,218 kg. Thrust (vac): 3,946,624 kgf. Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 5. F-1

• Stage Number: 2. 1 x Saturn MS-II-4(S)B Gross Mass: 494,100 kg. Empty Mass: 42,300 kg. Thrust (vac): 527,100 kgf. Isp: 421 sec. Burn time: 355 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 24.8 m. Propellants: Lox/LH2 No Engines: 5. J-2

• Stage Number: 3. 1 x Saturn MS-IVB-1 Gross Mass: 120,500 kg. Empty Mass: 13,900 kg. Thrust (vac): 105,200 kgf. Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 18.1 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.