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RD-103M
Part of Model 39 Family
Glushko LOx/Alcohol rocket engine. R-5M 8K51. First flight 1953.

AKA: 8D52M. Date: 1950-55. Number: 134 . Thrust: 500.10 kN (112,427 lbf). Unfuelled mass: 867 kg (1,911 lb). Specific impulse: 248 s. Specific impulse sea level: 220 s. Burn time: 120 s. Height: 3.22 m (10.57 ft). Diameter: 1.65 m (5.41 ft).

Thrust (sl): 432.000 kN (97,117 lbf). Thrust (sl): 44,052 kgf. Engine: 867 kg (1,911 lb). Chamber Pressure: 23.90 bar. Propellant Formulation: Lox/Alcohol-96%. Thrust to Weight Ratio: 58.82. Oxidizer to Fuel Ratio: 1.44.

Country: Russia. Engines: RD-103M. Launch Vehicles: R-5, R-5M, R-5A, R-5V, R-5B, R-5 VAO. Propellants: Lox/Alcohol. Agency: Glushko bureau.



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