RD-0210-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 1990's. Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
Engine: 570 kg (1,250 lb). Chamber Pressure: 147.00 bar. Thrust to Weight Ratio: 105.9. Oxidizer to Fuel Ratio: 2.6.
Related
- Country
- Russia
- Propellants
- Lox/Kerosene
- Agency
- Kosberg bureau