Shvetsov ASh-62
| ASh-62 | |
|---|---|
| |
| Shvetsov Ash-62 installed in a Lisunov Li-2. | |
| Type | Radial engine |
| Manufacturer | Shvetsov |
| First run | Template:Avyear |
| Number built | 40,631 |
| Developed from | Shvetsov M-25 |
The Shvetsov ASh-62 (designated M-62 before 1941) is a nine-cylinder, air-cooled, radial aircraft engine produced in the Soviet Union.
Design and development
The ASh-62 was a development of the R-1820 Cyclone that had been built in Russia under licence as the Shvetsov M-25, the main improvements including a two-speed supercharger and a more efficient induction system. Power was increased from the Cyclone's 775 hp to 1,000 hp. First run in 1937, licenced versions are still in production by WSK "PZL-Kalisz" in Poland as the ASz-62 (as of 2007). The Ash-62 was also produced in China. It is estimated that 40,361 were produced in the USSR.
Polish-built ASz-62IR engines are compatible with FAR-33 requirements. Further developments in Poland are the K9-AA, K9-BA and K9-BB engines, with take-off power of 1178 hp (860 kW), indicated power 698 kW.
The M-63 was an improved version of the M-62 with power output increased to 821 kW (1,100 hp) at 2,300 rpm for takeoff and 671 kW (900 hp) at 2,200 rpm at 4,500 m (14,764 ft) due to a greater compression ratio of 7.2:1 and a higher redline.
Applications
- de Havilland Canada DHC-3
- Neman R-10
- Polikarpov I-153
- Polikarpov I-16
- PZL-106 Kruk (some variants)
- PZL-Mielec M-18 Dromader
- PZL M-24 Dromader Super (K-9AA)
- Sukhoi Su-2
- Sukhoi Su-12
Specifications (M-62)
Data from [1]
General characteristics
- Type: Nine-cylinder single-row supercharged air-cooled radial engine
- Bore: 156 mm (6.12 in)
- Stroke: 175 mm (6.87 in)
- Displacement: 29.8 l (1,819 in³)
Components
- Valvetrain: Overhead valves
- Supercharger: Two-speed centrifugal type supercharger
- Fuel system: Carburetor
- Fuel type: 92 octane rating gasoline
- Cooling system: Air-cooled
Performance
- Power output: * 746 kW (1,000 hp) at 2,200 rpm for takeoff
- 634 kW (850 hp) at 2,100 rpm at 4,200 m (13,780 ft)
- Specific power: 25.03 kW/l (0.55 hp/in³)
- Compression ratio: 6.4:1
- Specific fuel consumption: 469 g/(kW•h) (0.77 lb/(hp•h))
- Power-to-weight ratio: 4.84 kW/kg (2.94 hp/lb)
References
Notes
- ^ Liss 1966, p. 9
Bibliography
- Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 154.
- Russian Aviation Museum
- Venik's Aviation
- Kotelnikov, Vladimir (2005). Russian Piston Aero Engines. Crowood Press Ltd. pp. p.119-122.
{{cite book}}:|pages=has extra text (help) - Liss, Witold (1966). The Polikarpov I-16 (Aircraft in Profile Number 122). Profile Publications Ltd.