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The Klimov M-106 was an experimental liquid-cooled V12 piston aircraft engine intended for Soviet aircraft during World War II.[1]


With the VK-105PF exhausting the potential of the M-105, Klimov prolonged its development into new VK-106 engine from 1941. Since air combat on the Eastern Front took place primarily at low altitudes (under 4,000 m {13,000 ft}), the new engine was built specifically for peak performance at those altitudes with a reduced compression ratio and a single-speed supercharger. Static testing was carried out from 27 October till 9 November 1942. Although reliable and easily installed in M-105-powered aircraft, VK-106 did not enter production because its cooling problems were not solved. Like M-105P, VK-106P could house an autocannon in the "vee" between the cylinder banks.


Specifications (VK-106-1sk)

Data from Kotelnikov[2]

General characteristics

  • Type: 12-cylinder supercharged liquid-cooled piston aircraft engine
  • Bore: 148mm (5.83 in)
  • Stroke: 170mm (6.69 in)
  • Displacement: 35.08 liters (2,140 in³)
  • Dry weight: 600 kg (1,320 lb)


  • Supercharger: Gear-driven single-stage single-speed centrifugal type supercharger
  • Fuel type: 95-octane rating gasoline
  • Cooling system: Liquid-cooled


  • Power output:
  • 1,007 kW (1,350 hp) at 2,600 rpm for takeoff
  • 1,007 kW (1,350 hp) at 2,000 m (6,560 ft)
  • Specific power: 28.8 kW/L (0.63 hp/in³)
  • Compression ratio: 6.5:1
  • Power-to-weight ratio: 1.68 kW/kg (1.02 hp/lb)

See also



  1. Gunston 1989, p. 90.
  2. Kotelnikov 2005, p. 142.


  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
  • Kotelnikov, Vladimir. Russian Piston Aero Engines. Marlborough, Wiltshire. The Crowood Press Ltd. 2005. ISBN 1-86126-702-9.

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