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RL-10A-4
Part of RL-10 Family
RL-10
RL-10
Credit: Lockheed Martin
Pratt and Whitney LOx/LH2 rocket engine. Out of production. Centaur stage for Atlas IIA, Atlas IIAS. First flight 1992.

Status: Out of production. Number: 106 . Thrust: 92.50 kN (20,795 lbf). Unfuelled mass: 168 kg (370 lb). Specific impulse: 449 s. Burn time: 392 s. Height: 2.29 m (7.51 ft). Diameter: 1.17 m (3.83 ft).

Engine: 168 kg (370 lb). Chamber Pressure: 39.12 bar. Area Ratio: 84. Thrust to Weight Ratio: 36.1735043478261. Oxidizer to Fuel Ratio: 5.5. Coefficient of Thrust vacuum: 1.74310161537244.



Country: USA. Launch Vehicles: Atlas IIA, Atlas IIAS. Propellants: Lox/LH2. Stages: Centaur IIA. Agency: Pratt and Whitney.

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