Encyclopedia Astronautica

Curtiss-Wright Lox/Gasoline rocket engine. Launch thrust 44.1 kN. Experimental unit for either missiles or piloted aircraft. Single thrust chamber, regnenerativey cooled and film cooled with water-alcohol mixture.

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.

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

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Associated Propellants
  • Lox/Gasoline Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Gasoline of various grades were used as fuel in the earliest rocket engines of Goddard and others. Once appropriate blends of kerosene were developed in the United States and Soviet Union, that became the hydrocarbon fuel of choice. More...

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