This page no longer updated from 31 October 2001. Latest version can be found at RD-120K

Manufacturer Name: RD-120K. Other Designations: RD-123. Designer: Glushko. Application: Soyuz M stage 1, 2. Proposed for X-34. Used on stages: Soyuz M-0, Soyuz M-1. Used on launch vehicles: Soyuz M. Propellants: Lox/Kerosene Thrust(vac): 89,000 kgf. Thrust(vac): 873.00 kN. Isp: 336 sec. Isp (sea level): 298 sec. Burn time: 305 sec. Mass Engine: 1,433 kg. Diameter: 1.5 m. Length: 2.8 m. Chambers: 1. Chamber Pressure: 172.00 bar. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Developed 1995-. References: 325 . Comments: Sea-level variant of RD-120. Thrust and Isp range due to throat diam. and chamber pressure. Gimbaling +/- 6 degree in two planes. Status 1996 was RD-120 prototype with 1.8 m diam., development estimated for three years. Chamber pressure 163 - 172 bar.
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Last update 12 March 2001.
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© Mark Wade, 2001 .