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BMW 132



BMW 132E

BMW took over the license for manufacturing air-cooled radial engines from US aircraft manufacturer Pratt & Whitney Aircraft Company on 3 January 1928. The nine-cylinder model Pratt & Whitney Hornet was initially manufactured virtually unchanged under the designation BMW Hornet. Soon BMW embarked on its own development. The result was the BMW 132 that went into production in 1933, which was essentially an improved version of the Hornet engine. A number of different versions were built. Aside from the carburetor designs used mainly in civilian aircraft, versions with direct fuel injection were manufactured for the German Luftwaffe. The engines had a displacement of 27.7 liters and generated up to 1,200 PS (880 kW)[citation needed], depending on model.

The 132 found widespread use in the transport role, remaining the primary powerplant of the Junkers Ju 52 for much of its life, turning the BMW 132 into one of the most important aero-engines for civilian aircraft during the 1930s.

Numerous pioneering flights were undertaken with the BMW 132. The most impressive was the first direct flight from Berlin to New York in a Fw 200 S-1 Condor equipped with four BMW 132 engines. It covered the distance to New York in 24 hours and 57 minutes on 10 August 1938.

Over 21,000 were built.


Arado Ar 196
Arado Ar 197
Blohm & Voss Ha 140
Blohm & Voss BV 141
Blohm & Voss BV 142
Fieseler Fi 98
Heinkel He 114
Heinkel He 115
Henschel Hs 123
Junkers Ju 160
Junkers Ju 52
Junkers Ju 86
Junkers W34


725 PS (715 hp, 533 kW)

132 Dc
Type: Nine-cylinder single-row supercharged air-cooled radial engine
Bore: 155.6 mm (6 1⁄8 in)
Stroke: 161.9 mm (6 3⁄8 in)
Displacement: 27.7 l (1,690 in³)
Length: 1,411 mm (55.55 in)
Diameter: 1,380 mm (54.33 in)
Dry weight: 525 kg (1,157 lb)
Valvetrain: Two overhead valves per cylinder
Supercharger: Single-speed centrifugal type supercharger
Fuel system: Hobson carburetor
Fuel type: 87 octane rating gasoline
Cooling system: Air-cooled
Reduction gear: Farman epicyclic gearing, 1.61:1
Power output:
589 kW (789 hp) for takeoff
581 kW (779 hp) at 2,290 rpm at 2,900 m (9,515 ft)
Specific power: 21.26 kW/l (0.47 hp/in³)
Compression ratio: 6.5:1
Specific fuel consumption: 322 g/(kW•h) (0.53 lb/(hp•h))
Oil consumption: 8-11 g/(kW•h) (0.21-0.28 oz/(hp•h))
Power-to-weight ratio: 1.12 kW/kg (0.68 hp/lb)

880 PS (868 hp, 647 kW)

960 PS (947 hp, 706 kW)

865 PS (853 hp, 636 kW)

730 PS (720 hp, 537 kW)



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