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Engine Model: Topaze. Designer: SEP. Propellants: N2O4/UDMH. Thrust(vac): 120.100 kN (27,000 lbf). Thrust(sl): 106.000 kN (23,829 lbf). Isp: 255 sec. Isp (sea level): 225 sec. Burn time: 39 sec. Mass Engine: 306 kg (674 lb). Diameter: 0.80 m (2.62 ft). Chambers: 1. Thrust to Weight Ratio: 40.02. Country: France. Status: Out of production. First Flight: 1965. Last Flight: 1967. Flown: 4.00.
Topaze used on Rocket Stages
- Used on stage: Topaze. on launch vehicle: VE.
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© Mark Wade, 1997 - 2008 except where otherwise noted.
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