Encyclopedia Astronautica

Curtiss-Wright Lox/Gasoline rocket engine. Launch thrust 266.83 kN. Turbine pump-fed, single thrust chamber unit intended for cancelled missile application. Engine designed to fit into the envelope dimensions of the German V-2!

Regnenerativey cooled and film cooled with water-alcohol mixture, spark plug igntion.

Application: cancelled project.


Thrust (sl): 266.830 kN (59,986 lbf). Thrust (sl): 27,210 kgf. Engine: 147 kg (324 lb). Propellant Formulation: Lox/Low octane gasoline+coolant water+alcohol.

AKA: XLR21-CW-1.
Unfuelled mass: 147 kg (324 lb).
Thrust: 266.83 kN (59,986 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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