Engineering:ATEC 212 Solo
| 212 Solo | |
|---|---|
| Role | Ultralight aircraft |
| National origin | Czech Republic |
| Manufacturer | ATEC v.o.s. |
| Status | In production |
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]
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)
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
- ↑ 1.0 1.1 1.2 1.3 Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 28. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
- ↑ 2.0 2.1 2.2 2.3 Tacke, Willi; Marino Boric; et al: World Directory of Light Aviation 2015-16, page 29. Flying Pages Europe SARL, 2015. ISSN 1368-485X
External links
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