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RD-213
Part of RD-107 Family
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.

Status: Development ended 1957. Date: 1956-57. Thrust: 755.00 kN (169,730 lbf). Unfuelled mass: 625 kg (1,377 lb). Specific impulse: 254 s. Specific impulse sea level: 231 s. Burn time: 110 s. Height: 2.50 m (8.21 ft). Diameter: 1.48 m (4.85 ft).

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.

Family: Storable liquid. Country: Russia. Spacecraft: Buran. Propellants: Nitric acid/Kerosene. Stages: Buran M-41. Agency: Glushko bureau. More at: 7509. Bibliography: 320, 344.



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