RD-108-8D75

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RD-108-8D75

Part of RD-107

R-7 aft end
Credit: © Mark Wade

Glushko LOx/Kerosene rocket engine. R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1. OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / LOx. Diameter is per chamber. First flight 1957.

AKA: 8D75. Number: 35 . Thrust: 912.00 kN (205,025 lbf). Unfuelled mass: 1,278 kg (2,817 lb). Specific impulse: 308 s. Specific impulse sea level: 241 s. Burn time: 340 s. Height: 2.86 m (9.38 ft). Diameter: 0.67 m (2.19 ft).

Chambers: 4. Thrust (sl): 713.600 kN (160,424 lbf). Thrust (sl): 72,768 kgf. Engine: 1,278 kg (2,817 lb). Chamber Pressure: 51.00 bar. Area Ratio: 18.9. Thrust to Weight Ratio: 72.76. Oxidizer to Fuel Ratio: 2.39.

Country: Russia. Launch Vehicles: Vostok 8K72, R-7. Propellants: Lox/Kerosene. Stages: Vostok 8K72-1, R-7 8K71-1. Agency: Glushko bureau.

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