This page no longer updated from 31 October 2001. Latest version can be found at RD-161-2

Manufacturer Name: RD-161 (2). Designer: Glushko. Propellants: Lox/Kerosene Thrust(vac): 2,030 kgf. Thrust(vac): 19.90 kN. Isp: 365 sec. Burn time: 900 sec. Mass Engine: 141 kg. Diameter: 1.0 m. Length: 2.2 m. Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 370.60. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Design concept 1990's. References: 318 . Comments: Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump.
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Last update 12 March 2001.
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© Mark Wade, 2001 .