To install click the Add extension button. That's it.

The source code for the WIKI 2 extension is being checked by specialists of the Mozilla Foundation, Google, and Apple. You could also do it yourself at any point in time.

Kelly Slayton
Congratulations on this excellent venture… what a great idea!
Alexander Grigorievskiy
I use WIKI 2 every day and almost forgot how the original Wikipedia looks like.
Live Statistics
English Articles
Improved in 24 Hours
Added in 24 Hours
What we do. Every page goes through several hundred of perfecting techniques; in live mode. Quite the same Wikipedia. Just better.

From Wikipedia, the free encyclopedia

Klimov VK-107A.jpg
VK-107A in Central Air Force Museum (Moscow)
Type V12 engine
National origin USSR
Manufacturer Klimov
First run 1942
Major applications
Developed from M-105 and VK-106
Developed into Klimov VK-108

The Klimov VK-107 was a V-12 liquid-cooled piston aircraft engine used by Soviet aircraft during World War II.[1]


The VK-107 was developed from the M-105 and VK-106. To achieve a greater power output, each cylinder now had four valves (two intake and two exhaust), crankshaft and camshafts were completely revised, and a new supercharger design was implemented. Although the engine could have been ready for production as early as 1942, the Soviets' factories lacked the capacity to produce a brand new design. Thus, the less powerful Klimov VK-105PF and VK-105PF2 V12 engines were built instead. However, the appearance of Luftwaffe Messerschmitt Bf 109G with Daimler-Benz DB 605 engine in 1943 created an urgent demand for a more powerful engine. VK-107A was put into production in 1944 and was used on Yak-9U fighters. The engine was not well liked by either pilots or mechanics – it had a life expectancy of only 25 hours and war emergency power was almost never used for fear of decreasing this even more. The engine was also difficult to service, in part because its exhaust headers were on the inside of the cylinder banks, the reverse placement of most V-type liquid-cooled engine designs.[2]


Data from Aircraft engines of the World 1953[3] and Russian piston aero engines[4]

(M-107P) Initial designation, produced 1941-1942; 686 built.
Prototypes with take-off rating of 1,080 kW (1,450 hp)
1942 production version without water-injection with military (high) rating of 1,100 kW (1,500 hp) at 2800 rpm and 4,500 m (14,800 ft), remained in production until 1948
with water injection
version for hybrid piston-motorjet powered Mikoyan-Gurevich I-250 (N) and Sukhoi Su-5 fighters
VK-107 coupled
A projected coupled powerplant driving contra-rotating propellers
attempt to further develop VK-107 with a rating of 1,380 kW (1,850 hp) for takeoff, used on several Yakovlev Yak-3 and Myasishchev DB-108 prototypes but did not enter production.
Boosted VK-108
1945-6 development of the VK-108, planned for use on the Myasishchev VB-109 bomber.


Specifications (VK-107B)

Data from Aircraft engines of the World 1953[3]

General characteristics

  • Type: 12-cylinder supercharged liquid-cooled Vee aircraft piston engine
  • Bore: 148 mm (5.8 in)
  • Stroke: 170 mm (6.7 in) one bank, 175 mm (6.9 in) the other due to the master/slave connecting-rod offset
  • Displacement: 35.08 l (2,141 cu in)
  • Length: 2,030 mm (80 in)
  • Width: 777 mm (30.6 in)
  • Height: 960 mm (38 in)
  • Dry weight: 620 kg (1,370 lb)
  • Power boost:Water injection for take-off and combat boost


  • Valvetrain: Two intake and two exhaust valves per cylinder actuated via an overhead camshaft
  • Supercharger: Single stage, two-speed, gear-driven centrifugal type supercharger with variable output impeeler driven at 7.85:1 and 10:1.
  • Fuel system: 6x K-105BP carburettors with automatic pressure regulation
  • Fuel type: 95 Octane
  • Oil system: Pressure feed at 5.9 bar (85 psi), Oil viscosity 20.5 centistokes (0.03177506355013 in2/s)
  • Cooling system: Liquid-cooled
  • Reduction gear: Spur gear 0.6:1 with hollow propeller shaft for cannon


  • Power output: Take-off (wet): 1,300 kW (1,800 hp) at 2,800 rpm / 53.1 in (1,350 mm) / +11.6 lb (5.3 kg) boost
Take-off (dry): 1,200 kW (1,600 hp) at 2,800 rpm / 52.4 in (1,330 mm) / +11.2 lb (5.1 kg) boost
Military (low): 1,200 kW (1,600 hp) at 2,800 rpm / 1,700 m (5,600 ft) altitude
Military (high): 1,100 kW (1,500 hp) at 2,800 rpm / 6,000 m (19,700 ft) altitude
Normal (low): 1,110 kW (1,490 hp) at 2,600 rpm / 2,000 m (6,600 ft) altitude
Normal (high): 1,010 kW (1,350 hp) at 2,600 rpm / 5,000 m (16,400 ft) altitude

See also

Related development

Comparable engines

Related lists


  1. ^ Gunston 1989, p.90.
  2. ^ Kotelnikov 2005, p. 143.
  3. ^ a b Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 315.
  4. ^ Kotelnikov, Vladimir (2005). Russian piston aero engines. Ramsbury, Wlits: Crowood. pp. 134, 142–143, 145, 183–184, 254. ISBN 1-86126-702-9.


  • 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.
This page was last edited on 16 January 2021, at 19:45
Basis of this page is in Wikipedia. Text is available under the CC BY-SA 3.0 Unported License. Non-text media are available under their specified licenses. Wikipedia® is a registered trademark of the Wikimedia Foundation, Inc. WIKI 2 is an independent company and has no affiliation with Wikimedia Foundation.