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.
- Anbo II (replica)
- Gribovsky G-15
- Gribovsky G-20
- Gribovsky G-21
- Gribovsky G-23
- Gribovsky G-27
- Kharkiv KhAI-3
- Laz-7M
- LWD Junak
- Mikoyan-Gurevich MiG-8 Utka
- Polikarpov Po-2
- PZL S-4 Kania
- Shavrov_Sh-2 amphibian
- Shcherbakov Shche-2
- Yakovlev UT-1
- Yakovlev UT-2
- Yakovlev Yak-6
- Yakovlev Yak-12
- Yakovlev Yak-18
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)
See also
Comparable engines
- Armstrong Siddeley Genet
- Armstrong Siddeley Mongoose
- Kinner K-5
- Walter Vega
- Warner Scarab Junior
- Wright R-540
Related lists
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.