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Plug-Nozzle SSME
Notional LOx/LH2 rocket engine. Study 1978. Used on VTOVL launch vehicle.

Status: Study 1978. Thrust: 3,728.70 kN (838,245 lbf). Unfuelled mass: 2,973 kg (6,554 lb). Specific impulse: 485 s. Specific impulse sea level: 412 s. Burn time: 500 s.

Thrust (sl): 3,167.400 kN (712,060 lbf). Thrust (sl): 322,992 kgf. Engine: 2,973 kg (6,554 lb). Area Ratio: 600. Thrust to Weight Ratio: 127.89.



Country: USA. Launch Vehicles: VTOVL 1978. Propellants: Lox/LH2. Stages: VTOVL 150t.

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