This page no longer updated from 31 October 2001. Latest version can be found at RD-0120M-CH

Manufacturer Name: RD-0120M-CH. Designer: Kosberg. Propellants: Lox/LCH4 Thrust(vac): 175,391 kgf. Thrust(vac): 1,720.00 kN. Isp: 372 sec. Mass Engine: 2,600 kg. Chambers: 1. Chamber Pressure: 186.00 bar. Oxidizer to Fuel Ratio: 3.40. Country: Russia. Status: Design concept 1990's. References: 342 . Comments: Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant.
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Last update 12 March 2001.
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© Mark Wade, 2001 .