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Viking 4
Part of Viking 2 Family
SEP N2O4/UDMH rocket engine. Used on Ariane 1, GSLV, PSLV. First flight 1979.

Number: 23 . Thrust: 721.00 kN (162,087 lbf). Unfuelled mass: 850 kg (1,870 lb). Specific impulse: 296 s. Specific impulse sea level: 200 s. Burn time: 132 s. Height: 3.68 m (12.07 ft). Diameter: 2.60 m (8.50 ft).

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.



Family: Storable liquid. Country: France. Launch Vehicles: Ariane 1, PSLV, GSLV. Propellants: N2O4/UDMH. Stages: Ariane 1-2, GSLV-2, PSLV-2. Bibliography: 225.

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