XJ40-WE-1

Designer: Wright. Propellants: Air/Kerosene. Thrust(vac): 48.500 kN (10,903 lbf). Thrust(sl): 48.500 kN (10,903 lbf). Isp: 1,800 sec. Burn time: 2,000 sec. Mass Engine: 850 kg (1,870 lb). Chambers: 1. Thrust to Weight Ratio: 5.81. Country: USA. Status: Out of production. First Flight: 1955. Last Flight: 1959. Flown: 30.

Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point.

XJ40-WE-1 used on Rocket Stages

Used on stage: Navaho X-10. on launch vehicle: Navaho X-10.

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