The Rotax 535 is an Austrian aircraft engine, that was designed and produced by Rotax of Gunskirchen for use in motor gliders.[1]
| 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 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
editThe 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
edit- 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
editSpecifications (535A)
editData 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
editRelated lists
References
edit- ^ a b c d e f g European Aviation Safety Agency, (26 February 2010), Type Certificate Data Sheet Number: E.209, retrieved 24 September 2015
- ^ Rotax. "Rotax Aircraft Engines - Product Range". flyrotax.com. Retrieved 24 September 2015.
- ^ Aircraft Owners and Pilots Association. "The Glaser-Dirks DG500M". aopa.org. Retrieved 24 September 2015.
