RD-161-2
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko LOx/Kerosene rocket engine. Design concept 1990's. Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump.
Engine: 141 kg (310 lb). Chamber Pressure: 117.70 bar. Area Ratio: 370.6. Thrust to Weight Ratio: 14.39. Oxidizer to Fuel Ratio: 2.6.
Related
- Country
- Russia
- Propellants
- Lox/Kerosene
- Agency
- Glushko bureau
- Bibliography
- 318