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RZ.2
Part of LR79 Family
Rolls Royce LOx/Kerosene rocket engine. Used on Europa launch vehicle. First flight 1964.

Number: 22 . Thrust: 836.30 kN (188,008 lbf). Unfuelled mass: 750 kg (1,650 lb). Specific impulse: 282 s. Specific impulse sea level: 248 s. Burn time: 156 s. Diameter: 1.53 m (5.00 ft).

Thrust (sl): 735.500 kN (165,347 lbf). Thrust (sl): 75,000 kgf. Engine: 750 kg (1,650 lb). Chamber Pressure: 39.46 bar. Area Ratio: 8. Thrust to Weight Ratio: 113.71. Coefficient of Thrust vacuum: 1.7615758510983. Coefficient of Thrust sea level: 1.55883890228938.



Country: UK. Launch Vehicles: Europa I. Propellants: Lox/Kerosene. Stages: Europa-1. Agency: Rolls Royce.

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