RL-10A-5KA

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RL-10A-5KA

Part of RL-10

Pratt and Whitney LOx/LH2 rocket engine. Kistler proposal. Design 1992. Throttleable to 30% of thrust, sea level version of RL10 with extendable nozzle for high altitude operation.

Status: Design 1992. Thrust: 100.49 kN (22,591 lbf). Unfuelled mass: 145 kg (319 lb). Specific impulse: 398 s. Specific impulse sea level: 352 s. Height: 1.19 m (3.92 ft). Diameter: 1.02 m (3.33 ft).

The RL-10A-5KA was proposed for use on the Kistler K-1 vehicle but was not selected.

Thrust (sl): 88.926 kN (19,991 lbf). Thrust (sl): 9,068 kgf. Engine: 145 kg (319 lb). Chamber Pressure: 40.81 bar. Area Ratio: 8.2. Thrust to Weight Ratio: 70.66. Oxidizer to Fuel Ratio: 6.

Country: USA. Propellants: Lox/LH2. Agency: Pratt and Whitney.

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