This page no longer updated from 31 October 2001. Latest version can be found at RL-10A-3A

RL-10 -

Credit: Lockheed Martin. 11,834 bytes. 146 x 231 pixels.

Designer: Pratt and Whitney. Used on stages: Centaur G, Centaur G Prime, Centaur G STS, Centaur I, Centaur II. Used on launch vehicles: Atlas G, Atlas I, Atlas II, Titan 4. Propellants: Lox/LH2 Thrust(vac): 7,485 kgf. Thrust(vac): 73.40 kN. Isp: 444 sec. Burn time: 550 sec. Mass Engine: 141 kg. Diameter: 1.0 m. Length: 1.8 m. Chambers: 1. Chamber Pressure: 32.31 bar. Area Ratio: 61.00. Oxidizer to Fuel Ratio: 5.00. Thrust to Weight Ratio: 53.24. Country: USA. Status: In Production. First Flight: 1984. Last Flight: 1999. Flown: 104. References: 500 .
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Last update 3 May 2001.
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© Mark Wade, 2001 .