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LR39
Reaction Motors LOx/Alcohol rocket engine. Small experimental engine. Single thrust chamber, water cooled, equipped only with spark plug ignition system and propellant flow valves. Test article only built.

AKA: D-50G1;XLR39-RM-1. Thrust: 225 N (50 lbf). Unfuelled mass: 0.66 kg (1.45 lb). Height: 0.22 m (0.73 ft). Diameter: 0.0380 m (0.1240 ft).

Engine: 0.66 kg (1.45 lb). Chamber Pressure: 16.70 bar. Propellant Formulation: Lox/Alcohol+Water mixture with .86 specific gravity. Thrust to Weight Ratio: 34.84.



Country: USA. Propellants: Lox/Alcohol. Agency: Reaction Motors.

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