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X45ALD-4000
Part of 40AL
Aerojet Nitric acid/Amine rocket engine. Development begun June 1948. Regenerative cooling, nitrogen pressure-fed, droppable but no recoverable. Early version using XLR-13-AJ-1 thrust chamber assembly.

AKA: XLR13-AJ-3. Date: June 1948. Thrust: 17.60 kN (3,957 lbf). Unfuelled mass: 403 kg (888 lb). Burn time: 60 s. Height: 4.50 m (14.70 ft). Diameter: 0.94 m (3.08 ft).

Thrust (sl): 17.600 kN (3,957 lbf). Thrust (sl): 1,800 kgf. Engine: 403 kg (888 lb). Chamber Pressure: 21.40 bar. Propellant Formulation: RFNA/70% Xylidine+30% AN-F-48.

Family: Storable liquid. Country: USA. Propellants: Nitric acid/Amine. Agency: Aerojet.
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