This page no longer updated from 31 October 2001. Latest version can be found at J-2-SL

Designer: Rocketdyne. Used on stages: Saturn II-SL. Used on launch vehicles: Saturn INT-19. Propellants: Lox/LH2 Thrust(vac): 101,634 kgf. Thrust(vac): 996.70 kN. Isp: 390 sec. Isp (sea level): 275 sec. Burn time: 310 sec. Mass Engine: 1,360 kg. Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 14.00. Country: USA. Status: Study 1966. Comments: Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use.
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Last update 12 March 2001.
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© Mark Wade, 2001 .