Siddeley Puma

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The Siddeley Puma was a British aero engine developed towards the end of World War I und produced by Siddeley-Deasy. First engines leaves the production lines of Siddeley-Deasy in Coventry in August 1917 an the production continues until December 1918. At least 4288 of 11500 ordered engines were delivered, then the orders where cancelled. Production was continued under the name Armstrong Siddeley Puma when the manufacturer was bought by Armstrong Whitworth and became Armstrong Siddeley.

[edit] Specifications

General characteristics

• Type: 6-cylinder water-cooled inline aircraft piston engine
• Bore: 5.7 in (145 mm)
• Stroke: 7.5 in (190 mm)
• Displacement: 1,147 in³ (18.8 L)
• Dry weight: 530 lb (240 kg)

Components

• Fuel system: Carburetor
• Cooling system: Water-cooled

Performance

• Power output:
  
  • 187 hp (140 kW) at 1,300 rpm for cruise
  • 243 hp (181 kW) at 1,450 rpm for short-term maximum power
• Specific power: 0.21 hp/in³ (9.6 kW/L)
• Fuel consumption:
  
  • 14 US gal/h (54 L/h) at cruise
  • 67 US gal/h (258 L/h) at short-term maximum power
• Power-to-weight ratio: 0.46 hp/lb (0.75 kW/kg)

[edit] References

• The Virtual Aviation Museum

[edit] See also

• List of aircraft engines