RD-108-8D75-1959
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko LOx/Kerosene rocket engine. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Used on Vostok 8K72K launch vehicle. First flight 1960.
Chambers: 4. Engine: 1,250 kg (2,750 lb). Chamber Pressure: 51.00 bar. Area Ratio: 18.9. Thrust to Weight Ratio: 76.8. Oxidizer to Fuel Ratio: 2.39.
Related
- Country
- Russia
- Launch Vehicles
- Vostok 8K72K
- Propellants
- Lox/Kerosene
- Stages
- Vostok 8K72K-1
- Agency
- Glushko bureau