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 C used on Rocket Stages Used on stage: Diamant B-1. on launch vehicle: Diamant B.                   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 - 2007 except where otherwise noted.

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