Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
Viking 4
Part of Viking 2
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.
Back to top of page
Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2019 Mark Wade - Contact
© / Conditions for Use