RL-10A-1 (original) (raw)

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RL-10A-1

Part of RL-10

RL-10
Credit: Lockheed Martin

Pratt and Whitney LOx/LH2 rocket engine. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961.

AKA: LR115. Number: 44 . Thrust: 66.70 kN (14,995 lbf). Unfuelled mass: 131 kg (288 lb). Specific impulse: 425 s. Specific impulse sea level: 10 s. Burn time: 430 s. Diameter: 1.53 m (5.00 ft).

Engine: 131 kg (288 lb). Chamber Pressure: 24.00 bar. Area Ratio: 47. Thrust to Weight Ratio: 51.9389312977099. Coefficient of Thrust vacuum: 2.04916270983758. Coefficient of Thrust sea level: 9.08293765042492E-02.

Country: USA. Launch Vehicles: Atlas Centaur LV-3C, Juno V-B, Saturn A-1, Saturn C-2, Saturn B-1, Saturn A-2, Saturn I. Propellants: Lox/LH2. Stages: Centaur C. Agency: Pratt and Whitney.

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