Viking 4
Engine · France
Original archive entry. The text, images and links below are kept as they were written.
SEP N2O4/UDMH rocket engine. Used on Ariane 1, GSLV, PSLV. First flight 1979.
Thrust (sl): 487.100 kN (109,504 lbf). Thrust (sl): 49,674 kgf. Engine: 850 kg (1,870 lb). Chamber Pressure: 54.00 bar. Area Ratio: 31. Thrust to Weight Ratio: 86.4917647058824. Oxidizer to Fuel Ratio: 1.7. Coefficient of Thrust vacuum: 1.80035299087596. Coefficient of Thrust sea level: 1.22627891680189.
Related
- Family
- Storable liquid
- Country
- France
- Propellants
- N2O4/UDMH
- Stages
- Ariane 1-2, GSLV-2, PSLV-2
- Bibliography
- 225