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Gross Mass: 1,360,800 kg (3,000,000 lb). Empty Mass: 108,900 kg (240,000 lb). Thrust (vac): 20,306.600 kN (4,565,105 lbf). Isp: 275 sec. Burn time: 163 sec. Propellants: Lox/Kerosene. Isp(sl): 253 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 48.78 m (160.03 ft). Country: USA. No Engines: 1. Engine: PF RP-1. Status: Study 1967. 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
Used on Launch Vehicles:
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