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RD-0120M-CH
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Manufacturer Name: RD-0120M-CH. Designer: Kosberg. Propellants: Lox/LCH4. Thrust(vac): 1,720.000 kN (386,670 lbf). Isp: 372 sec. Mass Engine: 2,600 kg (5,700 lb). Chambers: 1. Chamber Pressure: 186.00 bar. Oxidizer to Fuel Ratio: 3.40. Thrust to Weight Ratio: 67.45. Country: Russia. Status: Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant.
Bibliography and Further Reading - Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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