Engine Model: RD-212. Manufacturer Name: RD-212. Designer: Glushko. Developed in: 1952-56. Application: winged rocket M-40 (1). Propellants: Nitric acid/Kerosene. Thrust(vac): 623.000 kN (140,055 lbf). Throttled thrust(vac): 437.000 kN (98,241 lbf). Isp: 253 sec. Isp (sea level): 227 sec. Burn time: 100 sec. Mass Engine: 642 kg (1,415 lb). Diameter: 1.48 m (4.85 ft). Length: 2.50 m (8.20 ft). Chambers: 4. Chamber Pressure: 39.20 bar. Area Ratio: 7.20. Oxidizer to Fuel Ratio: 3.97. Thrust to Weight Ratio: 98.90. Country: Russia. Status: Developed 1952-56. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust and the RD-213 was developed in its place. Development to 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 28,4 / 39,2 bar.
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