This page no longer updated from 31 October 2001. Latest version can be found at RL-10A-4

RL-10 -

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

Designer: Pratt and Whitney. Used on stages: Centaur IIA. Used on launch vehicles: Atlas IIA, Atlas IIAS. Propellants: Lox/LH2 Thrust(vac): 9,433 kgf. Thrust(vac): 92.50 kN. Isp: 449 sec. Burn time: 392 sec. Mass Engine: 168 kg. Diameter: 1.2 m. Length: 2.3 m. Chambers: 1. Chamber Pressure: 39.12 bar. Area Ratio: 84.00. Oxidizer to Fuel Ratio: 5.50. Thrust to Weight Ratio: 36.17. Country: USA. Status: In Production. First Flight: 1992. Last Flight: 1999. Flown: 62. References: 500 .
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Last update 3 May 2001.
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© Mark Wade, 2001 .