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astronautix.com S5.3M


Other Designations: S5.3M. Designer: Isayev. Developed in: 1959-60, 1958-60. Application: R-9 (SS-8) missile stage 1. Propellants: Nitric acid/Amine Thrust(vac): 40,452 kgf. Thrust(vac): 396.70 kN. Isp (sea level): 241 sec. Mass Engine: 433 kg. Chambers: 4. Chamber Pressure: 66.00 bar. Area Ratio: 9.55. Oxidizer to Fuel Ratio: 3.60. Country: Russia. Status: Out of Production. References: 320 , 343 . Comments: Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level.
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Last update 12 March 2001.
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