Engine Model: 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.
J40 used on Rocket Stages