RL-10C-X Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 110.800 kN (24,909 lbf). Isp: 450 sec. Burn time: 630 sec. Mass Engine: 317 kg (700 lb). Diameter: 2.44 m (8.00 ft). Chambers: 1. Chamber Pressure: 102.00 bar. Area Ratio: 190.00. Thrust to Weight Ratio: 50.00. Country: USA. Status: Design concept 1994. RL-10C-X used on Rocket Stages Used on stage: Centaur C-X. RL-10C-X used on Spacecraft Used on: Centaur C-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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