287,296 Pages

M-11
Shvetsov M-11F

The Shvetsov M-11 is a five-cylinder air-cooled radial aircraft engine produced in the Soviet Union between 1923 and 1952.[1]

Design and development[edit | edit source]

The Shvetsov M-11 was designed under a 1923 competition in the Soviet Union for a new engine to power trainer aircraft. It is a single-row five-cylinder air-cooled radial piston engine with aluminum cylinder heads. Like the American Kinner B-5 5-cylinder radial of similar size, the M-11 had individual camshafts for each cylinder, operating the pushrods, rather than a single central cam ring. The initial versions of the M-11 suffered from a short service life of only 50 hours. The basic M-11 engine had a power output of 100 hp (73 kW), the newer M-11D variant was higher at 125 hp (92 kW). The ultimate version, M-11FR, introduced in 1946, increased power output to 160 hp at 1,900 rpm on takeoff and 140 hp at cruise and had provisions for a variable-pitch propeller, accessory drive (for vacuum pumps, compressors, generators, etc.) and featured a floatless carburetor.

Applications[edit | edit source]

The M-11 powered a number of aircraft, including the Polikarpov Po-2, Yakovlev UT-1, Yakovlev UT-2, Yakovlev Yak-6, Yakovlev Yak-12, Yakovlev Yak-18, Shcherbakov Shche-2 and Mikoyan-Gurevich MiG-8. It also powered the Polish LWD Junak, PZL S-4 Kania and Bulgarian Laz-7M (Лаз-7М ). The M-11 remained in production until 1952 with an estimated total of over 100,000 engines made. Several hundreds of M-11D and M-11FR-1 variants were manufactured under license in the Polish WSK-Kalisz works in Kalisz. It was also used for the up-engined GAZ-98K aerosani winter-used sled in a pusher configuration (as airboats use today), and as the standard powerplant for the similar NKL-26 propeller-driven sledges during the World War II years.

Specifications (M-11A)[edit | edit source]

Data from Kotelnikov[2]

General characteristics

  • Type: 5-cylinder air-cooled radial engine
  • Bore: 125mm (4.92 in)
  • Stroke: 140mm (5.51 in)
  • Displacement: 8.6 L (525 in3)
  • Dry weight: 165 kg (363 lb)

Components

  • Cooling system: Air-cooled

Performance

  • Power output:
  • 82 kW (110 hp) at 1,650 rpm for takeoff
  • 75 kW (100 hp) cruise
  • Specific power: 9.5 kW/L (0.21 hp/in³)
  • Compression ratio: 5.0:1
  • Power-to-weight ratio: 0.50 kW/kg (0.30 hp/lb)

See also[edit | edit source]

References[edit | edit source]

Notes[edit | edit source]

  1. Gunston 1989, p.158.
  2. Kotelnikov 2005, p.

Bibliography[edit | edit source]

  • 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 uses Creative Commons Licensed content from Wikipedia (view authors).
Community content is available under CC-BY-SA unless otherwise noted.