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RL-10A-5KA
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Designer: Pratt and Whitney. Application: Kistler proposal. Propellants: Lox/LH2. Thrust(vac): 100.488 kN (22,591 lbf). Thrust(sl): 88.926 kN (19,991 lbf). Isp: 398 sec. Isp (sea level): 352 sec. Mass Engine: 145 kg (319 lb). Diameter: 1.02 m (3.33 ft). Length: 1.19 m (3.92 ft). Chambers: 1. Chamber Pressure: 40.81 bar. Area Ratio: 8.20. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 70.66. Country: USA. Status: Design 1992. Throttleable to 30% of thrust, sea level version of RL10 with extendable nozzle for high altitude operation. The RL-10A-5KA was proposed for use on the Kistler K-1 vehicle but was not selected.
Bibliography and Further Reading - RL10 Derviative Options, Pratt and Whitney Fact Sheet, ca. 1995..
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