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Zenoah G-25


The Zenoah G-25 is a single cylinder, two stroke, carburetted aircraft engine from Japan, with optional fuel injection, designed for use on ultralight aircraft.

The Zenoah G-25 is equipped with single capacitor discharge ignition and a single Mikuni slide-type carburetor. It is equipped with a recoil starter system or optionally electric start and a 2.5 or 2.8:1 belt reduction drive.

The engine runs on a mixture of unleaded auto fuel and oil.
Producing 22 hp (16 kW) at 6600 rpm, the G-25 competed in the early 1980s ultralight powerplant market against the similar Rotax 277. Production of the engine was completed in the late 1980s and today only used engines and parts are available.


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Type: Single cylinder, two-stroke aircraft engine
Bore: 72 mm (2.8 in)
Stroke: 59.5 mm (2.3 in)
Displacement: 242 cc (14.78 cu in)
Length: 11.81 in (300.0 mm)
Width: 11.57 in (293.9 mm)
Height: 14.84 in (376.9 mm)
Dry weight: 51 lb (23.1 kg)
Ignition: CDI
Valvetrain: piston ported
Fuel type: unleaded auto fuel
Oil system: pre-mixed
Cooling system: free air
Reduction gear: 2.47 or 2.8:1 Poly-V belt system
Power output: 22 hp (16 kW) at 6600 rpm
Compression ratio: 6.5:1
Cycle: 2
No cylinders: 2
Bore: 72 mm
Stroke: 59.5 mm
Compression: 6.5
Displacement: 484 cc
Cooling: Air
Ignition: CDI
Reduction: Poly-V belt 2.47-1
Length: 11.81 in (300.0 mm)
Width: 11.57 in (293.9 mm)
Height: 14.84 in (376.9 mm)
Weight: 48 kg
Max pwr: 45 hp at 6600 rpm








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