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BMW VI
BMW VI at the Technik-Museum Berlin

The BMW VI was a water-cooled V-12 aircraft engine built in Germany in the 1920s. It was one of the most important German aero engines in the years leading up to World War II, with thousands built. It was further developed as the BMW VII and BMW IX, although these saw considerably less use.

Design and development[edit | edit source]

The VI was the first twelve-cylinder engine built by the BMW. It essentially consisted of two cylinder banks from the six-cylinder BMW IV bolted to a common cast aluminum crankcase at a a 60-degree included angle between the cylinder banks. Series production commenced in 1926 after type approval had been granted. From 1930 on, after 1000 engines of the BMW VI type had already been delivered, Germany was again permitted to construct military aircraft. The sudden additional demand resulted in the production figures increasing rapidly. In 1933 the BMW VI was used for BMW's first experiments with direct fuel injection.

The BMW VI was the chosen source of power for numerous record-breaking and long-distance flights, including an east-to-west crossing of the Atlantic in 1930 and a round-the world flight in 1932, both by Wolfgang von Gronau in an open Dornier Wal flying boat powered by two BMW VI engines.

The BMW VI was put to unusual use as a power unit for the "Rail Zeppelin" high-speed railcar. Many versions of the BMW VI engine were developed, and it was built under license in Japan and the Soviet Union. This was further evidence of the reliability of an engine with which BMW made a fundamental contribution to the build-up of German air transport. At least 9,200 were built between 1926 and 1938. The engine was license-built in the Soviet Union under the supervision of Mikulin, who then further developed it as the M-17. More license built engines were produced by Kawasaki Heavy Industries in Japan as the Kawasaki Ha-9.

Applications[edit | edit source]

Specifications (BMW VI)[edit | edit source]

Side view of the BMW VI

Data from de:BMW VI

General characteristics

  • Type: V-12
  • Bore: 160 mm (6.3 in)
  • Stroke: 190 mm (7.48 in)
  • Displacement: 45.84 L (2,797.5 cuin)
  • Length: 1810 mm (71.26 in)
  • Width: 859 mm (33.82 in)
  • Height: 1103 mm (43.43 in)
  • Dry weight: 510 kg (1124 lb)

Components

  • Fuel system: 2 x Zenith 60 DCL
  • Fuel type: min. 87 octane gasoline
  • Cooling system: Liquid-cooled

Performance

  • Power output: 650 HP 641 hp
  • Compression ratio: 5.50

See also[edit | edit source]

References[edit | edit source]

  • Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 25. 

External links[edit | edit source]

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