Shvetsov M-11
| M-11 | |
|---|---|
| |
| Shvetsov M-11F | |
| Type | Radial engine |
| Manufacturer | Shvetsov |
| First run | Template:Avyear |
| 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.
Applications
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)
Data from Kotelnikov.[2]
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
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.