RD-0256-Methane
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg LOx/LCH4 rocket engine. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.
Engine: 770 kg (1,690 lb). Chamber Pressure: 176.00 bar. Thrust to Weight Ratio: 110.71. Oxidizer to Fuel Ratio: 3.4.
Related
- Country
- Russia
- Propellants
- Lox/LCH4
- Agency
- Kosberg bureau