Encyclopedia Astronautica
XR5M12


XCOR Lox/CH4 rocket engine. 22.3 kN. First stages. Conceptual lox/methane rocket engine developed for a DARPA program through layout design phase, but never built.

The DARPA contract enabled XCOR to develop the methane cooling analysis tools used in later engine designs.

Application: First stages.

Status: Hardware.
Thrust: 22.30 kN (5,013 lbf).
First Launch: 2004-2006.

More... - Chronology...


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Associated Propellants
  • Lox/CH4 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. More...

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