DAR 21 Vector II
| DAR 21 Vector II | |
|---|---|
| General information | |
| Type | Ultralight aircraft |
| National origin | Bulgaria |
| Manufacturer | Aeroplanes DAR |
| Status | Production completed (2014) |
| History | |
| Manufactured | 2001-2014 |
| First flight | 1 August 2000 |
The DAR 21 Vector II is a Bulgarian ultralight aircraft, designed and produced by Aeroplanes DAR, first flying on 1 August 2000.[1]
When it was available the aircraft was supplied as a kit for amateur construction or as a complete ready-to-fly-aircraft.[2]
The aircraft was introduced in 2001 and production apparently ended in 2014, as by that year the aircraft was no longer advertised for sale by the company.[1][3][4]
Design and development
[edit | edit source]The aircraft was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a strut-braced high wing, a two-seats-in-tandem enclosed cockpit, conventional landing gear and a single engine in tractor configuration.[2]
The Vector II has riveted stressed skin made with 1050 and 3105 aluminum sheet for corrosion resistance. The fuselage has a square cross-section. Its 9.2 m (30.2 ft) span wing employs flaps that can be set to 15° for takeoff and 30° for landing. The standard engine available is the 64 hp (48 kW) Rotax 582 twin-cylinder, liquid-cooled, two-stroke powerplant, with the four-stroke 80 hp (60 kW) Rotax 912 optional. Solo flight is accomplished from the front seat.[2][5]
Variants
[edit | edit source]- DAR 21
- Standard version with bungee main landing gear suspension.[2]
- DAR 21S
- Upgraded version with aluminum sprung main landing gear suspension for increased ground clearance.[2]
Specifications (DAR 21)
[edit | edit source]Data from Bayerl and DAR[2][5]
General characteristics
- Crew: one
- Capacity: one passenger
- Length: 6.35 m (20 ft 10 in)
- Wingspan: 9.42 m (30 ft 11 in)
- Height: 1.80 m (5 ft 11 in)
- Wing area: 12.42 m2 (133.7 sq ft)
- Empty weight: 250 kg (551 lb)
- Gross weight: 450 kg (992 lb)
- Fuel capacity: 32 litres (7.0 imp gal; 8.5 US gal)
- Powerplant: 1 × Rotax 582 twin cylinder, liquid-cooled, two stroke, 48 kW (64 hp)
Performance
- Maximum speed: 200 km/h (120 mph, 110 kn)
- Cruise speed: 175 km/h (109 mph, 94 kn)
- Stall speed: 58 km/h (36 mph, 31 kn) at gross weight, flaps down
- Never exceed speed: 205 km/h (127 mph, 111 kn)
- g limits: +4/-2
- Rate of climb: 5 m/s (980 ft/min)
- Wing loading: 36.2 kg/m2 (7.4 lb/sq ft)
References
[edit | edit source]- ^ a b Lua error in Module:Citation/CS1/Configuration at line 2172: attempt to index field '?' (a nil value).
- ^ a b c d e f Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 20. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
- ^ Lua error in Module:Citation/CS1/Configuration at line 2172: attempt to index field '?' (a nil value).
- ^ Lua error in Module:Citation/CS1/Configuration at line 2172: attempt to index field '?' (a nil value).
- ^ a b Lua error in Module:Citation/CS1/Configuration at line 2172: attempt to index field '?' (a nil value).