This page no longer updated from 31 October 2001. Latest version can be found at RD-57A-1

Manufacturer Name: RD-57A-1. Designer: Lyulka. Developed in: 1995-98. Propellants: Lox/LH2 Thrust(vac): 40,279 kgf. Thrust(vac): 395.00 kN. Isp: 460 sec. Mass Engine: 550 kg. Diameter: 1.9 m. Length: 3.1 m. Chambers: 1. Area Ratio: 143.00. Oxidizer to Fuel Ratio: 5.80. Country: Russia. Status: Developed 1995-98. References: 332 . Comments: New version of RD-57M for SSTO-demonstrator proposed by Aerojet. Optimized nozzle contour for performance increase, new chamber material for weight reduction. First launch was planned for 3rd quarter 1998 in 1994, but not performed until 1999.
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Last update 12 March 2001.
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© Mark Wade, 2001 .