Viking

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Viking 2 Engine Model: Viking 2. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 693.000 kN (155,792 lbf). Thrust(sl): 611.600 kN (137,493 lbf). Isp: 281 sec. Isp (sea level): 248 sec. Burn time: 145 sec. Mass Engine: 776 kg (1,710 lb). Diameter: 0.95 m (3.11 ft). Length: 2.87 m (9.41 ft). Chambers: 1. Chamber Pressure: 55.00 bar. Area Ratio: 11.00. Thrust to Weight Ratio: 91.06. Country: France. Status: In production. First Flight: 1979. Last Flight: 2006. Flown: 60. Engine Model: Viking 2B. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 720.000 kN (161,860 lbf). Thrust(sl): 642.300 kN (144,395 lbf). Isp: 278 sec. Isp (sea level): 248 sec. Burn time: 205 sec. Mass Engine: 776 kg (1,710 lb). Diameter: 0.95 m (3.11 ft). Length: 2.87 m (9.41 ft). Chambers: 1. Chamber Pressure: 59.00 bar. Area Ratio: 11.00. Thrust to Weight Ratio: 86.38. Country: France. First Flight: 1984. Last Flight: 2003. Flown: 532. Engine Model: Viking 4. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 721.000 kN (162,087 lbf). Thrust(sl): 487.100 kN (109,504 lbf). Isp: 296 sec. Isp (sea level): 200 sec. Burn time: 132 sec. Mass Engine: 850 kg (1,870 lb). Diameter: 2.60 m (8.50 ft). Length: 3.68 m (12.07 ft). Chambers: 1. Chamber Pressure: 54.00 bar. Area Ratio: 31.00. Oxidizer to Fuel Ratio: 1.70. Thrust to Weight Ratio: 86.49. Country: France. First Flight: 1979. Last Flight: 2006. Flown: 23. Engine Model: Viking 4B. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 805.000 kN (180,971 lbf). Thrust(sl): 571.100 kN (128,388 lbf). Isp: 296 sec. Isp (sea level): 210 sec. Burn time: 125 sec. Mass Engine: 850 kg (1,870 lb). Diameter: 2.60 m (8.50 ft). Length: 3.51 m (11.51 ft). Chambers: 1. Chamber Pressure: 58.50 bar. Area Ratio: 30.80. Oxidizer to Fuel Ratio: 1.70. Thrust to Weight Ratio: 99.38. Country: France. First Flight: 1984. Last Flight: 2003. Flown: 133. Engine Model: Viking 5C. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 752.000 kN (169,056 lbf). Thrust(sl): 670.800 kN (150,802 lbf). Isp: 278 sec. Isp (sea level): 248 sec. Burn time: 142 sec. Mass Engine: 776 kg (1,710 lb). Diameter: 2.22 m (7.28 ft). Length: 2.87 m (9.41 ft). Chambers: 1. Chamber Pressure: 55.00 bar. Area Ratio: 11.00. Oxidizer to Fuel Ratio: 1.70. Thrust to Weight Ratio: 92.84. Country: France. First Flight: 1988. Last Flight: 2003. Flown: 238. Viking used on Rocket Stages Used on stage: Ariane 4L. on launch vehicle: Ariane. Used on stage: Ariane-1. on launch vehicle: Ariane. Used on stage: Ariane-2. on launch vehicle: Ariane. Used on stage: PSLV-2. on launch vehicle: GSLV. Used on stage: SLV Viking. on launch vehicle: GSLV. Used on stage: SLV Viking. on launch vehicle: PSLV. Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted.