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Alfa Romeo 126 R. C. 34
1935 - 1943



260

Description

The Alfa Romeo 126 was one of the most widely used aero engines in Italy from the mid-1930s until the end of the Second World War, powering almost all large multi-engined aircraft of its time. It was developed as an evolution of the model 125, retaining the same basic design: a nine-cylinder, air-cooled radial engine derived from the British Bristol Pegasus, for which a production licence had been acquired. Compared with the 125, Alfa Romeo introduced a number of modifications in the 126 aimed at improving performance and overall reliability. These included changes to the fuel system and the supercharger, which operated at higher pressures than those of contemporary engines from competing manufacturers. The 126 was produced in two versions: the R.C. 34, capable of delivering 750 hp at 3,400 metres above sea level, and, in smaller numbers, the R.C. 10, optimised for low-altitude operation, producing 800 hp at 1,000 metres. From the 126, Alfa Romeo derived several closely related engines incorporating various design and performance improvements, ranging from the model 127, intended for high-altitude use, to the more advanced and complex 131, which produced 940 hp. With appropriate modifications, the 126 was also used in a number of international competitions. Notable achievements include the seaplane distance record set by a Cant Z.506 B in 1937, and numerous successes with the SIAI-Marchetti S.M.79, including victory in the Istres–Damascus–Paris race in 1937 and the Rome–Dakar–Rio de Janeiro flight in 1938, completed at an average speed of 400 km/h.

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Technical specifications

ManufacturerAlfa Romeo, Portello, Milan, 1935 (pre-production), 1936–1943 (series production)
Type126
Description9-cylinder air-cooled radial aero engine; light-alloy crankcase constructed from two forged sections; steel cylinder barrels; aluminium-alloy pistons and cylinder heads; master-and-articulated connecting rod arrangement with a two-piece steel crankshaft, comprising a master rod and articulated rods
Stroke190 mm
Bore146 mm
Displacement28.6 litres
Compression ratio6.5
Power output780 hp at 2,185 rpm for take-off at sea level; 750 hp at 2,300 rpm at 3,400 m altitude
Specific power output26.2 hp/litre
Min. specific fuel consumption245 g/hp/h
Valvetrain system4 overhead valves per cylinder (two inlet, two exhaust), operated by pushrods and rocker arms
Fuel feeding systemPetrol (87 octane), with a twin-choke carburettor featuring automatic air–fuel mixture control
Supercharging systemSingle-stage centrifugal supercharger, gear-driven from the engine, with a drive ratio of 1:10
Ignition system2 spark plugs per cylinder supplied by two independent magnetos
Cooling systemAir-cooled
Lubrication systemForced, dry sump type, with gear-type pressure and scavenge pumps
Mass485 kg
Power-to-mass ratio0.62 kg/hp
Propeller speed ratio0.655 via a Farman reduction gear with straight-tooth bevel gears


Application

CANT Z 506

Caproni A.P.1 (Ca. 307)

SIAI Marchetti S.M. 73, S.M. 74, SM. 75, S.M. 79, S.M. 81, S.M. 83

 

Courtesy of the Historical Museum of the Italian Air Force, Vigna di Valle (Bracciano, Rome)

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