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Manufacturer Name: RD-212. Designer: Glushko. Developed in: 1952-56. Application: winged rocket M-40 (1). Propellants: Nitric acid/Kerosene Thrust(vac): 63,500 kgf. Thrust(vac): 623.00 kN. Isp: 253 sec. Isp (sea level): 227 sec. Burn time: 100 sec. Mass Engine: 642 kg. Diameter: 1.5 m. Length: 2.5 m. Chambers: 4. Chamber Pressure: 39.20 bar. Area Ratio: 7.20. Oxidizer to Fuel Ratio: 3.97. Country: Russia. Status: Developed 1952-56. References: 320 , 344 . Comments: Intended for acceleration of winged rocket, development to 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 28,4 / 39,2 bar.
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Last update 12 March 2001.
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