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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.[1][2]

212 Solo
Role	Ultralight aircraft Type of aircraft
National origin	Czech Republic
Manufacturer	ATEC v.o.s.
Status	In production

Design and development

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.[1][2]

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.[1][2]

Specifications (212 Solo)

Data from Bayerl[1][2]

General characteristics

• 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

• Maximum speed: 250 km/h (160 mph, 130 kn)
• Cruise speed: 220 km/h (140 mph, 120 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

External links

• Official website

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