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astronautix.com RD-0120-CH


Manufacturer Name: RD-0120-CH. Designer: Kosberg. Propellants: Lox/LCH4 Thrust(vac): 160,707 kgf. Thrust(vac): 1,576.00 kN. Isp: 363 sec. Mass Engine: 2,370 kg. Chambers: 1. Chamber Pressure: 172.50 bar. Oxidizer to Fuel Ratio: 3.40. Country: Russia. Status: Design concept 1990's. References: 342 . Comments: Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant.
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Last update 12 March 2001.
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