The CNA C.II was a small, air-cooled, two cylinder horizontally opposed aircraft engine designed and built in Italy in the late 1930s.

Type Horizontally opposed air-cooled twin
National origin Italy
Manufacturer Compagnia Nazionale Aeronautica (CNA)
Produced 1937-41



The low power, unsupercharged C.II had offset cylinders with special steel barrels and light alloy cylinder heads. The pistons were light alloy castings; the connecting rods were heat treated chrome-nickel steel, with split big ends. The CN.II had a one piece chrome-nickel steel crankshaft running in two roller bearings, with a ball thrust bearing. The crankcase was a one piece light alloy casting.[1]



Data from Erickson[2]



Data from Jane's All the World's Aircraft 1938[1]

General characteristics

  • Bore: 90 mm (3.54 in)
  • Stroke: 110 mm (4.33 in)
  • Displacement: 1.4 L (85.4 cu in)
  • Length: 478 mm (18.81 in)
  • Width: 856 mm (33.70 in)
  • Height: 526 mm (20.71 in)
  • Dry weight: dry 42 kg (92.6 lb)


  • Valvetrain: Large diameter overhead valves, one inlet and one exhaust per cylinder. Enclosed rocker gear operated by push-rods driven off upper crankcase camshaft.
  • Oil system: Wet sump; crankshaft fed pressurised oil by pump.
  • Cooling system: Air


  • Power output: rated 28 kW (38 hp) at 2,700 rpm at sea level


  1. ^ a b Grey, C.G. (1972). Jane's All the World's Aircraft 1938. London: David & Charles. p. 68d. ISBN 0715 35734 4.
  2. ^ Erickson, Jack. "Horizontally Opposed Piston Aero Engines: C.N.A." Retrieved 21 March 2012.