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RL-10A-5
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Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 64.700 kN (14,545 lbf). Thrust(sl): 54.800 kN (12,320 lbf). Isp: 373 sec. Isp (sea level): 316 sec. Burn time: 127 sec. Mass Engine: 143 kg (315 lb). Diameter: 1.02 m (3.33 ft). Length: 1.07 m (3.51 ft). 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. First Flight: 1993. Last Flight: 1996. Flown: 48. 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.
RL-10A-5 used on Rocket Stages - Used on stage: DC-X. on launch vehicle: DC-X.
- Used on stage: DC-Y. on launch vehicle: DC-Y.
Bibliography and Further Reading - RL10 Derviative Options, Pratt and Whitney Fact Sheet, ca. 1995..
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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