Encyclopedia Astronautica

Curtiss-Wright Lox/Gasoline rocket engine. 0.225 kN. Small experimental engine for ram-rocket tests. Single thrust chamber, regneratively cooled with gasoline, film cooling also used, spark plug ignition. Test article only built.

Chamber Pressure: 20.00 bar.

AKA: XLR37-CW-1.
Height: 0.23 m (0.75 ft).
Diameter: 0.0690 m (0.2260 ft).
Thrust: 225 N (50 lbf).
Burn time: 3,600 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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