RD-112

Engine · Russia

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

Glushko LOx/UDMH rocket engine. ICBM stage 1 (stage 2 was RD-113). Developed 1960.

Engine: 790 kg (1,740 lb). Chamber Pressure: 147.00 bar. Area Ratio: 31.8. Thrust to Weight Ratio: 140.56. Oxidizer to Fuel Ratio: 1.704.

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