This page no longer updated from 31 October 2001. Latest version can be found at RD-161P

Manufacturer Name: RD-161P. Designer: Glushko. Developed in: 1993-. Application: Soyuz M stage 3 (block LM). Propellants: H2O2/Kerosene Thrust(vac): 2,498 kgf. Thrust(vac): 24.50 kN. Isp: 319 sec. Burn time: 900 sec. Mass Engine: 105 kg. Diameter: 1.2 m. Length: 1.5 m. Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 265.00. Oxidizer to Fuel Ratio: 5.90. Country: Russia. Status: Developed 1993-. References: 318 . Comments: Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%.
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Last update 12 March 2001.
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© Mark Wade, 2001 .