RD-114

Engine · Russia

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

Glushko LOx/UDMH rocket engine. Used in ICBM stage 1 (stage 2 was RD-115). Developed 1961-65.

Engine: 990 kg (2,180 lb). Chamber Pressure: 147.00 bar. Area Ratio: 26.4. Thrust to Weight Ratio: 170.26. Oxidizer to Fuel Ratio: 1.77.

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