Armstrong-Siddeley Puma

From Biocrawler, the free encyclopedia.

The Armstrong-Siddeley Puma was an aero engine developed towards the end of the first world war.

Specifications

Cylinders: 6

Bore by stroke: 5.7 by 7.5 (145 by 190 mm)

Displacement: 18.8 l

Compression ratio:

HP: 243

Weight: 240 kg

short term max rpm: 1500

References

• The Virtual Aviation Museum (http://www.luftfahrtmuseum.com/htmi/itf/apuma.htm)

See also

• List of aircraft engines

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