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Plug-Nozzle SERV
Notional LOx/LH2 rocket engine. Study 1971. Used on Shuttle SERV launch vehicle.

Status: Study 1971. Thrust: 31,980.20 kN (7,189,435 lbf). Specific impulse: 455 s. Specific impulse sea level: 367 s. Burn time: 249 s.

Thrust (sl): 25,794.900 kN (5,798,924 lbf). Thrust (sl): 2,630,386 kgf.



Country: USA. Launch Vehicles: SERV. Propellants: Lox/LH2. Stages: Shuttle SERV-1.

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