This page no longer updated from 31 October 2001. Latest version can be found at Saturn LCB-Lox/RP-1

Gross Mass: 1,360,800 kg. Empty Mass: 108,900 kg. Thrust (vac): 2,070,700 kgf. Isp: 275 sec. Burn time: 163 sec. Propellants: Lox/Kerosene Isp(sl): 253 sec. Diameter: 6.6 m. Span: 9.3 m. Length: 48.8 m. Country: USA. No Engines: 1. PF RP-1 Status: Study 1967. Comments: 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 Lox/RFP-1 engine.
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Last update 12 March 2001.
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© Mark Wade, 2001 .