RD-0206

Engine · Russia

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

Kosberg N2O4/UDMH rocket engine. UR-200 stage 2. Developed 1961-64. Staged combustion cycle. First flight 1964.

Chamber Pressure: 147.00 bar. Area Ratio: 81.3. Oxidizer to Fuel Ratio: 2.6.

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