Engine Model: RD-213. Manufacturer Name: RD-213. Designer: Glushko. Developed in: 1956-57. Application: Winged rocket M-40 (2). Propellants: Nitric acid/Kerosene. Thrust(vac): 755.000 kN (169,730 lbf). Throttled thrust(vac): 549.000 kN (123,420 lbf). Isp: 254 sec. Isp (sea level): 231 sec. Burn time: 110 sec. Mass Engine: 625 kg (1,377 lb). Diameter: 1.48 m (4.85 ft). Length: 2.50 m (8.21 ft). Chambers: 4. Chamber Pressure: 46.60 bar. Area Ratio: 7.21. Oxidizer to Fuel Ratio: 3.97. Thrust to Weight Ratio: 123.20. Country: Russia. Status: Development ended 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level.
RD-213 used on Rocket Stages
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