RD-0242-HC

Engine · Russia

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

Kosberg LOx/Kerosene rocket engine. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Engine: 120 kg (260 lb). Chamber Pressure: 196.20 bar. Thrust to Weight Ratio: 106.21. Oxidizer to Fuel Ratio: 2.6.

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