This page no longer updated from 31 October 2001. Latest version can be found at RL-10A-1

RL-10 -

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

Designer: Pratt and Whitney. Used on stages: Centaur C. Used on launch vehicles: Atlas Centaur LV-3C, Juno V-B, Saturn A-1, Saturn A-2, Saturn B-1, Saturn C-2, Saturn I. Propellants: Lox/LH2 Thrust(vac): 6,804 kgf. Thrust(vac): 66.70 kN. Isp: 425 sec. Isp (sea level): 10 sec. Burn time: 430 sec. Mass Engine: 131 kg. Diameter: 1.5 m. Chambers: 1. Chamber Pressure: 24.00 bar. Area Ratio: 47.00. Thrust to Weight Ratio: 51.94. Country: USA. Status: Out of Production. First Flight: 1961. Last Flight: 1967. Flown: 44.
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Last update 12 March 2001.
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© Mark Wade, 2001 .