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Manufacturer Name: RD-252. Designer: Glushko. Developed in: 1961-66. Application: R-36-0 stage 2; Tsyklon 2 stage 2. Used on stages: R-36-0-2, Tsyklon 2-2. Used on launch vehicles: R-36-0, Tsyklon 2. Propellants: N2O4/UDMH Thrust(vac): 95,900 kgf. Thrust(vac): 940.50 kN. Isp: 317 sec. Burn time: 160 sec. Mass Engine: 715 kg. Diameter: 2.6 m. Length: 2.2 m. Chambers: 2. Chamber Pressure: 89.50 bar. Area Ratio: 46.10. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: In Production. First Flight: 1965. Last Flight: 1997. Flown: 133. References: 317 , 342 , 349 . Comments: Used modified chamber from RD-219, nozzle is conventional, so performance is higher.
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Last update 12 March 2001.
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