RD-0256-HC
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg LOx/Kerosene rocket engine. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
Engine: 770 kg (1,690 lb). Chamber Pressure: 172.00 bar. Thrust to Weight Ratio: 108.59. Oxidizer to Fuel Ratio: 2.6.
Related
- Country
- Russia
- Propellants
- Lox/Kerosene
- Agency
- Kosberg bureau