DOVA DV-1
| DOVA DV-1 Skylark | |
|---|---|
 Skylark, 2007 |
|
| Type: | Microlight |
| Design country: | |
| Manufacturer: |
DOVA |
| First flight: |
May 2000 |
| Commissioning: |
2002 |
| Production time: |
2002– |
| Number of pieces: |
50 |
The DOVA DV-1 Skylark is an ultralight touring aircraft produced by the Czech manufacturer DOVA Aircraft .
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history
The development of the Skylark by the Canadian professor David Marsden (a retired aerodynamics professor and avid pilot from Alberta, Canada) began in January 1999. The first flight of the prototype took place in May 2000. In May 2002 a contract was signed between Dr. Marsden and the Czech company DOVA Aircraft from Paskov closed after they were to take over responsibility for the approval and production of the Skylark in Europe. The construction, originally designed for the American LSA class , was also adapted by the company to the European UL building regulations. DOVA produces the kit for the aircraft for this. Finished aircraft (from the kits with approval and prototype support) are produced in Germany by UL-Bautechnik Grilz in Kamenz. The LSA version is produced by Skyviewaviation in California . The price of the machine starts at around 75,000 euros. In the meantime (as of March 2010) more than 50 machines have been built (25 of them in Germany), of which around 35 are in flight.
construction
The DV-1 is an all-metal single-engine, two-seat aircraft for cruising flight. The low-wing aircraft has a T-tail and is powered by a 100 hp Rotax 912 S. The propeller used is a three-bladed GRP that can be adjusted on the ground or, alternatively, an adjustable constant-speed Neuform propeller. The fuel is housed in two 45-liter containers in the wings. The wing profile was designed on the computer for the special aerodynamic requirements of ultralight aircraft. The profile of the trapezoidal structure is in three sections (laminar at the front, thick in the middle and heavily arched, optimized for good stall behavior at the rear) to meet different requirements (e.g. high safety in slow flight). Winglets were installed to improve flight performance . The landing flaps can be adjusted between 40 ° (when landing) and −10 ° (for high-speed flight). The non-retractable three-wheeled landing gear with steerable nose wheel is covered and partly made of fiberglass.
Technical specifications
| Parameter | Data |
|---|---|
| crew | 1-2 |
| length | 6.62 m |
| span | 8.14 m |
| height | 2.28 m |
| Wing area | 9.44 m² |
| payload | ? kg |
| Empty mass | 297 kg |
| Takeoff mass | 472.5 kg |
| Cruising speed | 210-240 km / h |
| Top speed | 267 km / h |
| Service ceiling | ? m |
| Range | ? km |
| Max. Rate of climb | 5.9 m / s at 110 km / h |
| Engines | a Rotax 912S, 100 PS (74 kW) |
See also
Web links
Individual evidence
- ↑ Manufacturer website (Skylark-UL)
- ↑ FliegerRevue April 2010, p. 34, Skylark from Canada