RD-213
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko Nitric acid/Kerosene rocket engine. Winged rocket M-40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level.
Chambers: 4. Throttled thrust(vac): 549.000 kN (123,420 lbf). Engine: 625 kg (1,377 lb). Chamber Pressure: 46.60 bar. Area Ratio: 7.21. Propellant Formulation: AK27I/TM-185. Thrust to Weight Ratio: 123.2. Oxidizer to Fuel Ratio: 3.97.
Related
- Family
- Storable liquid
- Country
- Russia
- Spacecraft
- Buran
- Propellants
- Nitric acid/Kerosene
- Stages
- Buran M-41
- Agency
- Glushko bureau