The CNA C.II was a small, air-cooled, two cylinder horizontally opposed aircraft engine designed and built in Italy in the late 1930s.
| C.II | |
|---|---|
| Type | Horizontally opposed air-cooled twin |
| National origin | Italy |
| Manufacturer | Compagnia Nazionale Aeronautica (CNA) |
| Produced | 1937-41 |
Design edit
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]
Applications edit
Data from Erickson[2]
Specifications edit
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)
Components
- 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
Performance
- Power output: rated 28 kW (38 hp) at 2,700 rpm at sea level
References edit
- ^ a b Grey, C.G. (1972). Jane's All the World's Aircraft 1938. London: David & Charles. p. 68d. ISBN 0715 35734 4.
- ^ Erickson, Jack. "Horizontally Opposed Piston Aero Engines: C.N.A." Retrieved 21 March 2012.