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Designer: Pratt and Whitney. Application: Kistler proposal. Propellants: Lox/LH2 Thrust(vac): 10,247 kgf. Isp: 398 sec. Isp (sea level): 352 sec. Mass Engine: 145 kg. Diameter: 1.0 m. Length: 1.2 m. Chambers: 1. Chamber Pressure: 40.81 bar. Area Ratio: 8.20. Oxidizer to Fuel Ratio: 6.00. Country: USA. Status: Design 1992. References: 500 . Comments: 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.
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Last update 3 May 2001.
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© Mark Wade, 2001 .