Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, Ni-250 Steel Hull.

LEO Payload: 39,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 1,986,700 kgf. Total Mass: 1,617,100 kg. Core Diameter: 6.6 m. Total Length: 70.0 m.

• Stage Number: 1. 1 x Saturn LCB-Storable-250 Gross Mass: 1,451,500 kg. Empty Mass: 108,900 kg. Thrust (vac): 2,165,100 kgf. Isp: 267 sec. Burn time: 163 sec. Isp(sl): 245 sec. Diameter: 6.6 m. Span: 9.3 m. Length: 40.7 m. Propellants: N2O4/UDMH No Engines: 1. PF N204/UDMH-2165k

• Stage Number: 2. 1 x Saturn IVB (S-IB) Gross Mass: 118,800 kg. Empty Mass: 12,900 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: 17.8 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