S1.5400A
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Korolev LOx/Kerosene rocket engine. Molniya 8K78M-3. First flight 1964.
Engine: 148 kg (327 lb). Chamber Pressure: 54.00 bar. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 46.25.
Related
- Country
- Russia
- Launch Vehicles
- Molniya 8K78M
- Propellants
- Lox/Kerosene
- Stages
- Molniya 8K78M-3
- Agency
- Korolev bureau