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Armstrong Siddeley Puma

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The Armstrong Siddeley Puma was an aero engine developed towards the end of World War I.

[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)

<h3>Components

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

<h3>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

[edit] See also


Armstrong Siddeley aero-engines
Piston
Leopard - Jaguar - Panther - Mongoose - Puma - Lynx - Cheetah - Nimbus
Turbojet
Sapphire
Turboprop
Double Mamba - Mamba - Python - Adder - Viper

v • d • e</div>

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