RL-10B-X Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 93.400 kN (20,997 lbf). Isp: 470 sec. Burn time: 408 sec. Mass Engine: 317 kg (700 lb). Diameter: 1.53 m (5.00 ft). Chambers: 1. Chamber Pressure: 102.04 bar. Area Ratio: 250.00. Thrust to Weight Ratio: 30.00. Country: USA. Status: Design concept 1994. RL-10B-X used on Rocket Stages Used on stage: Centaur B-X. RL-10B-X used on Spacecraft Used on: Centaur B-X.                   Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2007 except where otherwise noted.

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