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RD-108-11D512


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R-7 aft end
Credit: © Mark Wade Glushko LOx/Kerosene rocket engine. Soyuz 11A511-1, Soyuz 11A511U-1. Design 2000. Diameter is per chamber. First flight 1965.

AKA: 11D512. Status: Design 2000. Number: 752 . Thrust: 997.00 kN (224,134 lbf). Unfuelled mass: 1,400 kg (3,000 lb). Specific impulse: 315 s. Specific impulse sea level: 248 s. Burn time: 286 s. Height: 2.86 m (9.38 ft). Diameter: 0.67 m (2.19 ft).

Chambers: 4. Thrust (sl): 746.400 kN (167,797 lbf). Thrust (sl): 76,100 kgf. Engine: 1,400 kg (3,000 lb). Chamber Pressure: 51.00 bar. Thrust to Weight Ratio: 72.59.

Country: Russia. Launch Vehicles: Soyuz 11A511, Soyuz-U. Propellants: Lox/Kerosene. Stages: Soyuz 11A511-1, Soyuz 11A511U-1. Agency: Glushko bureau. Bibliography: 173, 21, 225, 287. Photo Gallery RD-107
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