Plug-Nozzle SSME Propellants: Lox/LH2. Thrust(vac): 3,728.700 kN (838,245 lbf). Thrust(sl): 3,167.400 kN (712,060 lbf). Isp: 485 sec. Isp (sea level): 412 sec. Burn time: 500 sec. Mass Engine: 2,973 kg (6,554 lb). Chambers: 1. Area Ratio: 600.00. Thrust to Weight Ratio: 127.89. Country: USA. Status: Study 1978. Plug-Nozzle SSME used on Rocket Stages Used on stage: VTOVL 150t. on launch vehicle: VTOVL.                   Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2007 except where otherwise noted.

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