This page no longer updated from 31 October 2001. Latest version can be found at RL-10A-5

Designer: Pratt and Whitney. Used on stages: DC-X, DC-Y. Used on launch vehicles: DC-X. Propellants: Lox/LH2 Thrust(vac): 6,696 kgf. Thrust(vac): 64.70 kN. Isp: 373 sec. Isp (sea level): 316 sec. Burn time: 127 sec. Mass Engine: 143 kg. Diameter: 1.0 m. Length: 1.1 m. Chambers: 1. Chamber Pressure: 39.12 bar. Area Ratio: 4.00. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 46.85. Country: USA. Status: Out of Production. First Flight: 1994. Last Flight: 1996. Flown: 8. References: 500 .

Throttleable to 30% of thrust, sea level version of RL10. Four engines were built and were used on the DC-X and the upgraded DC-XA VTOVL SSTO launch vehicle demonstrators. The DC-Y was a conceptual vehicle design and did not use these engines. The RL-10A-5KA was proposed for use on the Kistler K-1 vehicle but was not selected.

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Last update 3 May 2001.
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© Mark Wade, 2001 .