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Engine Model: Vexin A. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 68.600 kN (15,422 lbf). Thrust(sl): 59.500 kN (13,376 lbf). Isp: 277 sec. Isp (sea level): 240 sec. Burn time: 96 sec. Mass Engine: 175 kg (385 lb). Diameter: 0.50 m (1.64 ft). Chambers: 1. Thrust to Weight Ratio: 40.00. Country: France. First Flight: 1964. Last Flight: 1971. Flown: 44.
Engine Model: Vexin B. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 75.400 kN (16,951 lbf). Thrust(sl): 66.400 kN (14,927 lbf). Isp: 251 sec. Isp (sea level): 221 sec. Burn time: 100 sec. Mass Engine: 192 kg (423 lb). Diameter: 0.34 m (1.10 ft). Chambers: 1. Thrust to Weight Ratio: 40.04. Country: France. Status: Out of production. First Flight: 1965. Last Flight: 1967. Flown: 16.
Engine Model: Vexin C. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 99.100 kN (22,279 lbf). Thrust(sl): 87.300 kN (19,626 lbf). Isp: 251 sec. Isp (sea level): 221 sec. Burn time: 110 sec. Mass Engine: 252 kg (555 lb). Diameter: 0.35 m (1.14 ft). Chambers: 1. Thrust to Weight Ratio: 40.11. Country: France. Status: Out of production. First Flight: 1970. Last Flight: 1973. Flown: 20.
Vexin used on Rocket Stages
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