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Liberty-1
Notional LOx/Kerosene rocket engine. Development ended 1988. Pressure-fed engine. Used on Liberty launch vehicle.

Status: Development ended 1988. Thrust: 245.20 kN (55,123 lbf). Unfuelled mass: 270 kg (590 lb). Specific impulse: 270 s. Specific impulse sea level: 230 s. Burn time: 157 s. Diameter: 1.58 m (5.18 ft).

Thrust (sl): 208.800 kN (46,940 lbf). Thrust (sl): 21,296 kgf. Engine: 270 kg (590 lb). Area Ratio: 5. Thrust to Weight Ratio: 92.59.



Country: USA. Launch Vehicles: Liberty. Propellants: Lox/Kerosene. Stages: Liberty 1.

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