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LR19
Curtiss-Wright LOx/Gasoline rocket engine. Experimental unit for either missiles or piloted aircraft. Single thrust chamber, regeneratively cooled and film cooled with water-alcohol mixture.

AKA: XLR19-CW-1. Thrust: 44.10 kN (9,914 lbf). Unfuelled mass: 268 kg (590 lb). Burn time: 120 s. Height: 3.35 m (10.99 ft). Diameter: 0.81 m (2.65 ft).

Turbo-pump with sufficient capacity to reach 7300 kgf.

Thrust (sl): 44.100 kN (9,914 lbf). Thrust (sl): 4,500 kgf. Engine: 268 kg (590 lb). Chamber Pressure: 25.50 bar. Propellant Formulation: Lox/Low octane gasoline+coolant water+alcohol.



Country: USA. Propellants: Lox/Gasoline. Agency: Curtiss-Wright.

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