Encyclopedia Astronautica
XJ40-WE-1


Wright turbojet engine. 48.5 kN. Out of production. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1800s. Used on Navaho X-10 launch vehicle. First flight 1955.

Thrust (sl): 48.500 kN (10,903 lbf). Thrust (sl): 4,943 kgf. Engine: 850 kg (1,870 lb). Thrust to Weight Ratio: 5.81.

Status: Out of production.
Unfuelled mass: 850 kg (1,870 lb).
Thrust: 48.50 kN (10,903 lbf).
Specific impulse: 1,800 s.
Burn time: 2,000 s.
Number: 30 .

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Associated Countries
See also
Associated Launch Vehicles
  • Navaho X-10 American intermediate range cruise missile. Reusable, conventional airfield takeoff-and-landing aerodynamic test vehicle for Navaho missile. More...

Associated Manufacturers and Agencies
  • Wright American manufacturer of rocket engines. Wright, USA. More...

Associated Propellants
  • Air/Kerosene Ambient air (78 % nitrogen, 21% oxygen, etc.) is scooped up by air intakes and used in turbojet, turbofan, ramjet, scramjet, or other airbreathing engines. It is used to burn aviation-grade kerosene, commercial grade JP-4 or JP-5, their military equivalents, or special high-temperature blends such as those used in the SR-71. More...

Associated Stages
  • Navaho X-10 Air/Kerosene propellant rocket stage. Loaded/empty mass 19,183/11,700 kg. Thrust 96.95 kN. Specific impulse 1800 seconds. Aerodynamic test vehicle for Navaho missile; Max speed Mach 2.08; range 1320 km. More...

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