This page no longer updated from 31 October 2001. Latest version can be found at RL-10C-X

Designer: Pratt and Whitney. Used on stages: Centaur C-X. Propellants: Lox/LH2 Thrust(vac): 11,300 kgf. Thrust(vac): 110.80 kN. Isp: 450 sec. Burn time: 630 sec. Mass Engine: 317 kg. Diameter: 2.4 m. Chambers: 1. Chamber Pressure: 102.00 bar. Area Ratio: 190.00. Thrust to Weight Ratio: 50.00. Country: USA. Status: Design concept 1994.
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Last update 12 March 2001.
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© Mark Wade, 2001 .