Rotax 447
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The Rotax 447 is a Script error: No such module "convert"., inline 2-cylinder, two-stroke aircraft engine, built by BRP-Rotax GmbH & Co. KG of Austria for use in ultralight aircraft.[1][2]
Design and development
The Rotax 447 is a development of the Rotax 377, increasing the power output from Script error: No such module "convert". to Script error: No such module "convert". by increasing the cylinder bore from 62 mm to 67.5 mm and the maximum rpm from 6500 to 6800.[2] The modern 447 has a single breakerless, magneto capacitor-discharge ignition (CDI) system. Early (ca. 1988) models use a breaker point ignition system.
The Rotax 447 features piston-ported, air-cooled cylinder heads and cylinders, utilizing either a fan or free air for cooling. Lubrication is by use of pre-mixed fuel and oil. The engine can be equipped with either one or two piston-type float carburetors. The dual-carburetor version uses Bing model 84 carburetors. The single-carburetor version uses a Bing model 54 carburetor. An optional High Altitude Compensation kit is available.[1][2] It is typically installed with an induction-pulse-driven diaphragm fuel pump to provide fuel pressure.
The engine's propeller drive is via a Rotax type B gearbox. The standard engine includes a muffler exhaust system with an extra after-muffler as optional. The standard starter is a recoil start type, with an electric starter optional. An integral alternating current generator producing 170 watts at 12 volts with external rectifier-regulator is optional. The engine includes an intake air filter and can be fitted with an intake silencer system.[1][2]
The manufacturer acknowledges the design limitations of this engine, warning pilots:[1]
Variants
- 447 UL-1V
- basic engine equipped with a single carburettor, Script error: No such module "convert". at 6800 rpm[2]
- 447 UL-2V
- basic engine equipped with two carburettors, Script error: No such module "convert". at 6800 rpm[2]
Applications
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Specifications (447)
Data from OPERATORS MANUAL FOR ENGINE TYPES 447, 503 & 582[1]
General characteristics
- Type: two-stroke air-cooled aeroengine
- Bore: 67.5 mm (2.66 in)
- Stroke: 61 mm (2.4 in)
- Displacement: 426.5 cc (26.64 cu in)
- Dry weight: 26.8 kg (59 lb) (dry, no exhaust system)
Components
- Valvetrain: piston ports
- Fuel system: pneumatic pump pressurized
- Fuel type: regular autofuel
- Oil system: premixed in the fuel at 50:1 or oil injection
- Cooling system: fan or free air
- Reduction gear: Rotax 'B' gearbox: 2.00, 2.24, 2.58 ratios
Performance
- Power output: Script error: No such module "convert". at 6800 rpm
- Compression ratio: 9.6 (theoretical) 6.3 (effective)
- Fuel consumption: 11 litres/hr (3 US gph)
- Power-to-weight ratio: 1.12 kW/kg (0.68 hp/lb)
References
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