Rotax 582

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The Rotax 582 is a 48 kW (64 hp) two-stroke, two-cylinder, rotary intake valve, oil-in-fuel or oil injection pump, liquid-cooled, gear reduction-drive aircraft engine manufactured by BRP-Rotax GmbH & Co. KG. It is for use in non-certified aircraft operating in day visual flight rules.

Development

The Rotax 582 is based upon the earlier Rotax 532 engine design and was designed for use ultralight aircraft.[1][2] The 582 increased the bore from the 532 engine's 72 to 76 mm (2.8 to 3.0 in) and increased the stroke from 61 to 64 mm (2.4 to 2.5 in). This increased the displacement from 521.2 cc (31.81 cu in) to 580.7 cc (35.44 cu in), an increase of 11%. The increased displacement had the effect of flattening out the 532's torque curve and allowed the 582 to produce useful power over a wider rpm range. Reliability over the 532 was also improved.[2]

The 582 features liquid-cooled cylinder heads and cylinders with a Rotary Intake Valve. Cooling is via an externally-mounted radiator. Lubrication is either by use of pre-mixed fuel and oil or oil injection from an externally-mounted oil tank. The 582 has dual independent breakerless, magneto capacitor discharge ignition (CDI) systems and is equipped with two piston-type carburetors. It uses a manifold-driven pneumatic fuel pump to provide fuel pressure. An optional High Altitude Compensation kit is available.[1][2]

The engine's propeller drive is via a Rotax type B, C or E style 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]

Limitations

The manufacturer acknowledges the design limitations of this engine, warning pilots:[1]

"This engine, by its design, is subject to sudden stoppage. Engine stoppage can result in crash landings, forced landings or no power landings. Such crash landings can lead to serious bodily injury or death...This is not a certificated aircraft engine. It has not received any safety or durability testing, and conforms to no aircraft standards. It is for use in experimental, uncertificated aircraft and vehicles only in which an engine failure will not compromise safety. User assumes all risk of use, and acknowledges by his use that he knows this engine is subject to sudden stoppage...Never fly the aircraft equipped with this engine at locations, airspeeds, altitudes, or other circumstances from which a successful no-power landing cannot be made, after sudden engine stoppage. Aircraft equipped with this engine must only fly in DAYLIGHT VFR conditions."[1]

Applications

Blue Yonder EZ Flyer showing its Rotax 582 engine installation, including the radiator suspended below the engine.
Mainair Blade 582
A Warp Drive Inc propeller mounted to a Rotax 582 on a Quad City Challenger II.

Specifications (Rotax 582)

Rotax 582 installation

General characteristics

  • Type: two-cylinder, two-stroke, rotary valve, oil-in-fuel or oil-injected lubrication, dual carburetors, electronic dual ignition
  • Bore: 76 mm (2.99 in)
  • Stroke: 64 mm (2.52 in)
  • Displacement: 580.7 cm³ (35.44 cu in)
  • Dry weight: 50 kg 110 lb with electric starter, carburetors, fuel pump, air filters and reduction gear

Components

  • Fuel type: premium unleaded: RON 90 octane or higher leaded or unleaded or AVGAS 100 LL
  • Oil system: oil-in-fuel (pre-mix) or oil injection
  • Cooling system: liquid cooled

Performance

  • Power output: 48 kW 64.4 HP SAE @ 6,500 RPM 1-minute
  • Compression ratio: 11.5 (theoretical) - 5.75 effective

See also

References

  1. ↑ 1.0 1.1 1.2 1.3 1.4 BRP-Rotax GmbH & Co. KG (2006). "OPERATORS MANUAL FOR ENGINE TYPES 447, 503 & 582". Retrieved 2009-03-09. 
  2. ↑ 2.0 2.1 2.2 2.3 Raisner, William: LEAF catlog, pages 6-105. Leading Edge Airfoils, 1995.

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