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Plug-Nozzle J-2
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Designer: Rocketdyne. Propellants: Lox/LH2. Thrust(vac): 6,864.600 kN (1,543,223 lbf). Thrust(sl): 5,330.100 kN (1,198,254 lbf). Isp: 425 sec. Isp (sea level): 330 sec. Burn time: 260 sec. Chambers: 1. Country: USA. Status: Study 1993. Plug nozzle version of J-2 proposed for certain Saturn V upgrades in late 1960's.
Plug-Nozzle J-2 used on Rocket Stages - Used on stage: DC-I. on launch vehicle: DC-Y.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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