RD-0120-CH

Engine · Russia

Original archive entry. The text, images and links below are kept as they were written.

Kosberg LOx/LCH4 rocket engine. Design concept 1990's. Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant.

Engine: 2,370 kg (5,220 lb). Chamber Pressure: 172.50 bar. Thrust to Weight Ratio: 67.8. Oxidizer to Fuel Ratio: 3.4.

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