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Plug-Nozzle Rombus
Notional LOx/LH2 rocket engine. Study 1964. Used on Rombus launch vehicle.

Status: Study 1964. Thrust: 101,988.00 kN (22,927,814 lbf). Specific impulse: 459 s. Specific impulse sea level: 359 s. Burn time: 215 s.

Thrust (sl): 79,768.100 kN (17,932,582 lbf). Thrust (sl): 8,134,205 kgf.



Country: USA. Launch Vehicles: Rombus. Propellants: Lox/LH2. Stages: Rombus core.

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