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25AL-1000

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AKA: XLR1-AJ-1. Date: May 1942. Thrust: 4.41 kN (991 lbf). Unfuelled mass: 109 kg (240 lb). Burn time: 25 s. Height: 1.40 m (4.50 ft). Diameter: 0.90 m (2.95 ft).

Three spherical propellant tanks, fixed installation, single uncooled thrust chamber, pressure fed, permanent installed in tail cone of engine nacelle.

Thrust (sl): 4.410 kN (991 lbf). Thrust (sl): 450 kgf. Engine: 109 kg (240 lb). Chamber Pressure: 20.00 bar. Propellant Formulation: RFNA/Aniline.