DST-25
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Isayev N2O4/UDMH rocket engine. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 300,000 ignitions
Engine: 0.90 kg (1.98 lb). Chamber Pressure: 8.00 bar. Area Ratio: 45. Thrust to Weight Ratio: 2.83. Oxidizer to Fuel Ratio: 1.85.
Related
- Family
- Storable liquid
- Country
- Russia
- Propellants
- N2O4/UDMH
- Agency
- Isayev bureau
- Bibliography
- 350