This page no longer updated from 31 October 2001. Latest version can be found at RD-113

Manufacturer Name: RD-113. Designer: Glushko. Developed in: 1960. Application: ICBM stage 2 (stage 1 was RD-112). Propellants: Lox/UDMH Thrust(vac): 116,044 kgf. Thrust(vac): 1,138.00 kN. Isp: 360 sec. Mass Engine: 1,100 kg. Diameter: 2.5 m. Length: 4.2 m. Chambers: 1. Chamber Pressure: 147.00 bar. Area Ratio: 119.80. Oxidizer to Fuel Ratio: 1.70. Country: Russia. Status: Developed 1960. References: 320 . Comments: Upper stage version of RD-112 with larger nozzle.
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Last update 12 March 2001.
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© Mark Wade, 2001 .