This page no longer updated from 31 October 2001. Latest version can be found at RD-0256-Methane

Manufacturer Name: RD-0256-Methan. Designer: Kosberg. Developed in: 1996-. Propellants: Lox/LCH4 Thrust(vac): 85,248 kgf. Thrust(vac): 836.00 kN. Isp: 353 sec. Mass Engine: 770 kg. Chambers: 1. Chamber Pressure: 176.00 bar. Oxidizer to Fuel Ratio: 3.40. Country: Russia. Status: Design concept 1996-. References: 342 . Comments: Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.
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Last update 12 March 2001.
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© Mark Wade, 2001 .