Shvetsov M-11

M-11
	Shvetsov M-11F
Type	Radial engine
Manufacturer	Shvetsov
First run	1923
Number built	100,000+

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

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.

Variants

Data from:^[2]

M-100: Designation of prototype and initial designs.
M-11: Initial production version at 75 kW (100 hp), compression ratio 5:1
M-11a: 75 kW (100 hp) / 82 kW (110 hp)
M-11/A: 75 kW (100 hp) / 82 kW (110 hp)
M-11B: 75 kW (100 hp) / 82 kW (110 hp)
M-11D: 86 kW (115 hp) / 93 kW (125 hp)
M-11E: Compression ratio 6:1 - 110 kW (150 hp) / 120 kW (160 hp)
M-11F: 108 kW (145 hp) / 123 kW (165 hp)
M-11FM: 108 kW (145 hp)
M-11FR: Compression ratio 5.5:1 - 100 kW (140 hp) / 120 kW (160 hp)
M-11FR-1: Compression ratio 5.5:1 - 100 kW (140 hp) / 120 kW (160 hp)
M-11FN: 150 kW (200 hp)
M-11G: 75 kW (100 hp) / 82 kW (110 hp)
M-11I: Compression ratio 5.5:1 - 130 kW (170 hp) / 150 kW (200 hp)
M-11K: 86 kW (115 hp) / 93 kW (125 hp)
M-11L: 86 kW (115 hp) / 93 kW (125 hp)
M-11M: 108 kW (145 hp)
M-11V: 75 kW (100 hp) / 82 kW (110 hp); M-11Ya:A projected development of the M-11 at GAZ-41. The prototype was run but results were unsatisfactory, re-designated M-12
M-11Ye: Developed by Okromechko 110 kW (150 hp)

Further developments

3M-11: An alternative designation for the M-50 three cylinder derivative of the M-11
M-12: A 190 hp (140 kW) development of the M-11 by M.A. Kossov, un-related to the NAMI-100, which had been earlier designated M-12.
M-12 (M-11Ya): A projected development of the M-11 at GAZ-41. The prototype was run but results were unsatisfactory, re-designated from M-11Ya
M-13 (M-13K): A 1944 development by M.A. Kossov to be assembled from various M-11 variants
M-13: In parallel with the M-13K, E.V. Urmin at GAZ-41 mated cylinders from the M-11D with new crankshaft and crankcase
M-13: A later M-13 was created by I.A. Muzhilov at OKB-41 in 1946. Despite passing state acceptance test in June 1948, this engine was not put into production.
M-48: A 7-cylinder further development at GAZ-29 150 kW (200 hp)
M-49: A 9-cylinder further development at GAZ-29 200 kW (270 hp) / 230 kW (310 hp)
M-50: A 3-cylinder further development at GAZ-29 45 kW (60 hp)
M-51: A 5-cylinder further development at GAZ-29 93 kW (125 hp) / 108 kW (145 hp)
MG-11: Development of the M-51 at the NIIGVF (Nauchno-Issledovatel'skiy Institut Grazdahnskovo Vozdooshnovo Flota - civil air fleet scientific test institute) by M.A. Kossov. 110 kW (150 hp) / 130 kW (180 hp)
MG-21: Development of the M-48 at the NIIGVF by M.A. Kossov. 160 kW (210 hp) / 190 kW (250 hp)
MG-31: Development of the M-49 at the NIIGVF by M.A. Kossov. 200 kW (270 hp) / 240 kW (320 hp)
MG-50: A projected 18 cylinder, two-row radial derived from M-11 components by M.A. Kossov. 600 kW (800 hp) / 630 kW (850 hp)

Applications

The M-11 powered a number of Soviet, Bulgarian and Polish aircraft. 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, and as the standard powerplant for the similar NKL-26 propeller-driven sledges during the World War II years.

Specifications (M-11A)

Data from Kotelnikov.^[3]

General characteristics

Type: 5-cylinder air-cooled radial engine
Bore: 125 mm (4.92 in)
Stroke: 140 mm (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: 5:1
Power-to-weight ratio: 0.5 kW/kg (0.3 hp/lb)

References

Notes

^ Gunston 1989, p.158.
^ Kotelnikov, Vladimir (2005). Russian Piston Aero Engines. Marlborough: The Crowood Press Ltd. ISBN 978-1-86126-702-3.
^ Kotelnikov 2005, p.

Bibliography

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.

[1] Gunston 1989, p.158.

[Kotelnikov-2] Kotelnikov, Vladimir (2005). Russian Piston Aero Engines. Marlborough: The Crowood Press Ltd. ISBN 978-1-86126-702-3.

[3] Kotelnikov 2005, p.

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