RB-211-22B

Designer: Rolls Royce. Propellants: Air/Kerosene. Thrust(vac): 29.400 kN (6,609 lbf). Thrust(sl): 26.700 kN (6,002 lbf). Isp: 9,900 sec. Burn time: 4,590 sec. Mass Engine: 4,180 kg (9,210 lb). Chambers: 1. Thrust to Weight Ratio: 0.71. Country: UK. First Flight: 1990. Last Flight: 2006. Flown: 117.

Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust.

RB-211-22B used on Rocket Stages

Used on stage: L-1011. on launch vehicle: Pegasus.

Used on stage: L-1011. on launch vehicle: Pegasus XL.

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