RD-103M
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko LOx/Alcohol rocket engine. R-5M 8K51. First flight 1953.
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.
Related
- Country
- Russia
- Engines
- RD-103M
- Propellants
- Lox/Alcohol
- Agency
- Glushko bureau