This page no longer updated from 31 October 2001. Latest version can be found at RD-161-1

Manufacturer Name: RD-161 (1). Designer: Glushko. Propellants: Lox/Kerosene Thrust(vac): 2,000 kgf. Thrust(vac): 19.60 kN. Isp: 360 sec. Burn time: 900 sec. Mass Engine: 119 kg. Diameter: 0.8 m. Length: 1.7 m. Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 351.60. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Design concept 1990's. References: 318 . Comments: Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump.
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Last update 12 March 2001.
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© Mark Wade, 2001 .