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.

Vexin A used on Rocket Stages

 
 
 
 
 
 
 
 
 
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