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Shvetsov M-62 / Ash-62 / Ash-63
Harbin / Dongan HS-5
PZL-Kalisz ASz-62




The ASh-62 (designated M-62 before 1941) was a development of the Wright R-1820 Cyclone that had been built in Russia under licence as the Shvetsov M-25. A nine-cylinder, air-cooled, radial aircraft engine, the main improvements included 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 were still in production by WSK "PZL-Kalisz" in Poland as the ASz-62 (as of 2007). The Ash-62 was also produced in China as the HS-5. 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.


Shvetsov Ash-62 installed in a Lisunov Li-2


Antonov An-2
Antonov An-6
Lisunov Li-2
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


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)
Length: 47.76 in (1,213 mm)
Diameter: 54.25 in (1,378 mm)
Dry weight: 560kg (1,235 lb)
Valvetrain: Overhead valves
Supercharger: Two-speed centrifugal type supercharger
Fuel system: Carburetor
Fuel type: 92 RON, 87 (R+M)/2 (AKI) octane rating gasoline
Cooling system: Air-cooled
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: 1.3 kW/kg (.81 hp/lb)


ASz-62 IR
Cylinder: 9
Capacity: 1823
Take-Off Power: 1000 HP at 2200 RPM       
Max TO power: 5 min
Fuel flow at Max TO pwr: 110 gph  
Rated Power: 820 HP at 2100 RPM
Max. Continuous: 738 HP at 2030 RPM
75% Power: 615 HP at 1910 RPM
50% Cruise: 410 HP at 1670 RPM
Fuel flow at 50% Cruise: 45 gph
Propellor Gear Ratio: 0.637 to 1 / 11:16
Typical climb: 1800 RPM and 800 mm Hg manifold pressure
Typical cruise: 1600 RPM and 700 mm Hg
Fuel: 100 Octane Aviation Grade minimum




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