Agusta GA.40

Agusta GA.40
Type	2-cylinder, air-cooled, horizontally opposed aircraft engine
National origin	Italy
Manufacturer	Agusta
Designer	M. Ginnini
First run	1955

The Agusta GA.40 was a 2-cylinder, air-cooled, horizontally opposed engine developed in Italy by Agusta for light aircraft use. It was intended for use in motorgliders. The engine was produced in the 1950s and 1960s. ^[1]

Specifications

Data from Jane's All the World's Aircraft 1962-63 ^[2]

General characteristics

• Type: 2-cylinder air-cooled horizontally opposed aircraft piston engine
• Bore: 100 mm (3.94 in)
• Stroke: 95 mm (3.74 in)
• Displacement: 1.492 L (91.05 in³)
• Length: 613 mm (24.13 in)
• Width: 785 mm (30.91 in)
• Height: 450 mm (17.72 in)
• Dry weight: 56 kg (123 lb) dry
• Designer: M. Ginnini

Components

• Valvetrain: pushrod operated overhead valve, 1x inlet + 1x exhaust per cylinder
• Fuel system: Stromberg NAS 3A1 carburettor
• Fuel type: 80/87 octane
• Oil system: Pressure lubrication with a gear driven pump
• Cooling system: Air-cooled

Performance

• Power output: 31.32 kW (42 hp) at 2,700rpm
• Specific power: 20.99 kW/L (0.46 hp/in³)
• Power-to-weight ratio: 0.559 kW/kg (0.34 hp/lb)

Applications

• Corby Starlet
• Kokkola Ko-04

Notes

1. Flight. July 1957.
2. Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.

References

• Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.