Neha Patil

ATEC 212 Solo

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Top speed  250 km/h
Manufacturer  ATEC v.o.s.
Wingspan  7.48 m
ATEC 212 Solo ATEC 212 Solo Untitled Aviation Photo 1841373 Airlinersnet

Atec 212 solo


The ATEC 212 Solo is a Czech ultralight aircraft, designed and produced by ATEC v.o.s. of Libice nad Cidlinou. The aircraft is supplied as a complete ready-to-fly-aircraft.

Contents

Design and development

ATEC 212 Solo ATEC 212 Solo Untitled Aviation Photo 1841373 Airlinersnet

The aircraft was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a cantilever low-wing, a single-seat, enclosed cockpit with a bubble canopy, fixed conventional landing gear and a single engine in tractor configuration.

ATEC 212 Solo ATEC 212 Solo Large Preview AirTeamImagescom

The 212 Solo is made from carbon fibre and was derived from the ATEC 321 Faeta and ATEC 122 Zephyr 2000 designs. Its 7.48 m (24.5 ft) span wing employs an SM701 airfoil and slotted flaps. Standard engines available are the 64 hp (48 kW) Rotax 582 two-stroke and the 80 hp (60 kW) Rotax 912UL four-stroke powerplant.

Specifications (212 Solo)

Data from Bayerl

General characteristics

ATEC 212 Solo wwwaerogloborguserfilesEncyclopediaAAtecvos
  • Crew: one
  • Wingspan: 7.48 m (24 ft 6 in)
  • Wing area: 7.27 m2 (78.3 sq ft)
  • Empty weight: 200 kg (441 lb)
  • Gross weight: 315 kg (694 lb)
  • Fuel capacity: 50 litres (11 imp gal; 13 US gal)
  • Powerplant: 1 × Rotax 582 twin cylinder, liquid-cooled, two stroke, 48 kW (64 hp)
  • Propellers: 3-bladed composite
  • Performance

    ATEC 212 Solo ATEC ATEC 212 SOLO
  • Maximum speed: 250 km/h (155 mph; 135 kn)
  • Cruising speed: 220 km/h (137 mph; 119 kn)
  • Stall speed: 65 km/h (40 mph; 35 kn)
  • Rate of climb: 7 m/s (1,400 ft/min)
  • Wing loading: 43.32 kg/m2 (8.87 lb/sq ft)
  • References

    ATEC 212 Solo Wikipedia


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