RD-212
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko Nitric acid/Kerosene rocket engine. Developed 1952-56. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD-213 was developed instead.
Development to 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 28,4 / 39,2 bar.
Chambers: 4. Throttled thrust(vac): 437.000 kN (98,241 lbf). Engine: 642 kg (1,415 lb). Chamber Pressure: 39.20 bar. Area Ratio: 7.2. Propellant Formulation: AK27I/TM-185. Thrust to Weight Ratio: 98.9. Oxidizer to Fuel Ratio: 3.97.
Related
- Family
- Storable liquid
- Country
- Russia
- Propellants
- Nitric acid/Kerosene
- Agency
- Glushko bureau