Viking 2 (original) (raw)

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Viking 2

Viking 2

SEP N2O4/UDMH rocket engine. In production. Used on Ariane 1, GSLV space launchers. First flight 1979.

Status: In production. Number: 60 . Thrust: 693.00 kN (155,792 lbf). Unfuelled mass: 776 kg (1,710 lb). Specific impulse: 281 s. Specific impulse sea level: 248 s. Burn time: 145 s. Height: 2.87 m (9.41 ft). Diameter: 0.95 m (3.11 ft).

Thrust (sl): 611.600 kN (137,493 lbf). Thrust (sl): 62,366 kgf. Engine: 776 kg (1,710 lb). Chamber Pressure: 55.00 bar. Area Ratio: 11. Thrust to Weight Ratio: 91.0631443298969. Coefficient of Thrust vacuum: 1.77769748966301. Coefficient of Thrust sea level: 1.57769748966301.

Subtopics

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

Viking 2B SEP N2O4/UDMH rocket engine. Used on Ariane 2/3. First flight 1984.

Viking 4B SEP N2O4/UDMH rocket engine. Used on Ariane 4. First flight 1984.

Viking 5C SEP N2O4/UDMH rocket engine. Used on Ariane 42L, Ariane 44L, Ariane 44LP. First flight 1988.

Family: Storable liquid. Country: France. Launch Vehicles: Ariane 1, GSLV. Propellants: N2O4/UDMH. Stages: Ariane 1-1, GSLV-0.

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