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astronautix.com S2.720


Other Designations: S2.720. Designer: Isayev. Application: Engine for SAM-missile V-755. Propellants: Nitric acid/Amine Thrust(vac): 3,498 kgf. Thrust(vac): 34.30 kN. Isp (sea level): 233 sec. Burn time: 55 sec. Mass Engine: 48 kg. Diameter: 0.5 m. Length: 0.9 m. Chambers: 1. Chamber Pressure: 64.00 bar. Oxidizer to Fuel Ratio: 3.23. Country: Russia. Status: Out of Production. References: 225 , 329 , 340 , 342 . Comments: Pump-fed engine. Used in engine unit of a special apparatus. Pump-fed engine. 20,4 kN sea level.
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Last update 12 March 2001.
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© Mark Wade, 2001 .