Rotax 535
Type Aircraft engine
National origin Austria
Manufacturer Rotax
First run circa 1982
Major applications Glaser-Dirks DG-500M
Schempp-Hirth Janus
Schempp-Hirth Nimbus-4

The Rotax 535 is an Austrian aircraft engine, that was designed and produced by Rotax of Gunskirchen for use in motor gliders.[1]

The first application for type certification to JAR 22, Appendix H, was made on 29 June 1982 and the first certification was granted on 27 April 1983.[1] It is out of production and is no longer offered for sale by Rotax.[2]

Design and development

The Rotax 535 is a twin cylinder two-stroke, in-line, 521.2 cc (31.8 cu in) displacement, liquid-cooled, gasoline engine design, with a 3:1 belt reduction drive. It employs dual Bosch or Ducati magnetic high-voltage condenser ignition systems, one or two carburetors and produces a maximum of 60 hp (45 kW) at 7200 rpm. It runs on 96 octane automotive gasoline or 100LL avgas. Lubrication is 50:1 super two stroke oil premixed with the fuel.[1]

Variants

535A
Equipped with twin Tillotson HR or Mikuni BN 38 diaphragm carburetors and a Mikuni DF 44 diaphragm fuel pump. Produces 60 hp (45 kW) at 7200 rpm. First certified on 27 April 1983.[1]
535B
Equipped with twin Tillotson HR or Mikuni BN 38 diaphragm carburetors and a Mikuni DF 44 diaphragm fuel pump. Produces 55 hp (41 kW) at 7200 rpm. First certified on 27 April 1983.[1]
535C
Equipped with one Mikuni BN 38 diaphragm carburetor and a Mikuni DF 44 diaphragm fuel pump. Produces 60 hp (45 kW) at 7200 rpm. First certified on 12 June 1987.[1]

Applications

Specifications (535A)

Data from EASA Type Certificate[1]

General characteristics

  • Type: Twin cylinder, two stroke aircraft engine
  • Bore: 72 mm (2.8 in)
  • Stroke: 64 mm (2.5 in)
  • Displacement: 521.2 cc (31.8 cu in)

Components

  • Fuel system: 2 x Tillotson HR or Mikuni BN 38 diaphragm carburetors, with a Mikuni DF 44 diaphragm fuel pump
  • Fuel type: 96 octane automotive gasoline or 100LL avgas
  • Oil system: 50:1 super two stroke oil premixed with fuel
  • Cooling system: liquid
  • Reduction gear: 3:1 belt reduction drive

Performance

  • Power output: 60 hp (45 kW)
  • Fuel consumption: 100% power approximately 29 L/h (7.67 gal/h), 75% power approximately 22 L/h (5.82 gal/h)

See also

Related lists

References

  1. 1 2 3 4 5 6 7 European Aviation Safety Agency, (26 February 2010), Type Certificate Data Sheet Number: E.209, retrieved 24 September 2015
  2. ↑ Rotax. "Rotax Aircraft Engines - Product Range". flyrotax.com. Retrieved 24 September 2015.
  3. ↑ Aircraft Owners and Pilots Association. "The Glaser-Dirks DG500M". aopa.org. Retrieved 24 September 2015.
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