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RL-10 -

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

Designer: Pratt and Whitney. Used on stages: Centaur D/E. Used on launch vehicles: Atlas Centaur SLV-3C, Atlas Centaur SLV-3D, Saturn IB-A, Saturn IB-CE, Saturn V-Centaur, Titan 3BAS2, Titan 3E, Titan 3L2, Titan 3L4. Propellants: Lox/LH2 Thrust(vac): 6,690 kgf. Thrust(vac): 65.60 kN. Isp: 444 sec. Burn time: 470 sec. Mass Engine: 131 kg. Diameter: 1.5 m. Length: 2.5 m. Chambers: 1. Chamber Pressure: 28.00 bar. Area Ratio: 57.00. Oxidizer to Fuel Ratio: 5.00. Thrust to Weight Ratio: 51.07. Country: USA. Status: Out of Production. First Flight: 1967. Last Flight: 1983. Flown: 112. References: 225 .
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Last update 12 March 2001.
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© Mark Wade, 2001 .