RD-107-8D74-1959
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. Diameter is per chamber. Used on Vostok 8K72K launch vehicle. First flight 1960.
Chambers: 4. Engine: 1,155 kg (2,546 lb). Chamber Pressure: 58.60 bar. Area Ratio: 18.9. Thrust to Weight Ratio: 87.87. Oxidizer to Fuel Ratio: 2.47.
Related
- Country
- Russia
- Launch Vehicles
- Vostok 8K72K
- Propellants
- Lox/Kerosene
- Stages
- Vostok 8K72K-0
- Agency
- Glushko bureau