RD-251
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
NPO Enerogmash Museum, November 1992
Credit: © Dietrich Haeseler
Glushko N2O4/UDMH rocket engine. R-36-0 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD-250-type units. First flight 1965.
Chambers: 6. Thrust (sl): 2,366.000 kN (531,897 lbf). Thrust (sl): 241,300 kgf. Engine: 1,729 kg (3,811 lb). Chamber Pressure: 83.30 bar. Area Ratio: 14.7. Thrust to Weight Ratio: 156.15. Oxidizer to Fuel Ratio: 2.6.
Related
- Family
- Storable liquid
- Country
- Russia
- Launch Vehicles
- Tsiklon, R-36O 8K69, Tsiklon-2, R-36 8K67P
- Propellants
- N2O4/UDMH
- Stages
- R-36-1, R-36-0-1, Tsyklon 2-1
- Agency
- Glushko bureau