DAR 21 Vector II

The DAR 21 Vector II is a Bulgarian ultralight aircraft, designed and produced by Aeroplanes DAR, first flying on 1 August 2000.[1]

DAR 21 Vector II
Role Ultralight aircraft
National origin Bulgaria
Manufacturer Aeroplanes DAR
First flight 1 August 2000
Status Production completed (2014)
Produced 2001-2014

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

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
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)

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
  1. Aeroplanes DAR (2014). "Company History". Retrieved 21 September 2015.
  2. Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 20. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
  3. "Internet Archive Wayback Machine". archive.org. Retrieved 11 September 2015.
  4. Aeroplanes DAR (2014). "DAR 21". Archived from the original on November 17, 2013. Retrieved 21 September 2015.
  5. Aeroplanes DAR (2012). "DAR-21". Archived from the original on 17 November 2013. Retrieved 22 April 2012.
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