Thor T/A
| T/A | |
|---|---|
| Role | Ultralight aircraft |
| National origin | Canada |
| Manufacturer | Thor-Air Inc |
| Designer | Thorsten B. Strenger (or possibly Gunter Webster) |
| Introduction | 1985 |
| Status | Production completed |
|
| |
The Thor T/A is a Canadian ultralight aircraft that was designed by Thorsten B. Strenger (or possibly Gunter Webster) and produced by Thor-Air of Weston, Ontario. The aircraft was supplied as a kit for amateur construction.[1][2]
Design and development
The aircraft was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of 254 lb (115 kg). The aircraft has a standard empty weight of 238 lb (108 kg). It features a strut-braced high-wing, a single-seat, open cockpit, conventional landing gear and a single engine in tractor configuration.[1][2]
The aircraft is made from bolted-together aluminum tubing, with its flying surfaces covered in Dacron sailcloth. Its 80% double-surface 32.3 ft (9.8 m) span wing is braced with "V" lift struts. The pilot is accommodated on an open seat, protected by a simple windshield. The landing gear has suspension on the main wheels and features a steerable tailwheel. The three axis control system is unusual. Pitch and roll are conventionally controlled with elevator and rudder, while roll is controlled with tip rudders.[1][2]
Variants
- T/A
- Initial design, powered by a 28 hp (21 kW) Rotax 277 single cylinder, two-stroke powerplant.[1]
- 1-A
- Up-engined model, powered by a 40 hp (30 kW) Rotax 447 twin cylinder, two-stroke powerplant.[1]
- Two-seater
- Similar to the single-seat models but with a second seat for dual instruction.[1]
Specifications (T/A)
Data from Cliche and the Virtual Ultralight Museum[1][2]
General characteristics
- Crew: one
- Length: 13.8 ft (4.2 m)
- Wingspan: 32 ft 4 in (9.86 m)
- Height: 7 ft 8 in (2.34 m)
- Wing area: 167 sq ft (15.5 m2)
- Empty weight: 238 lb (108 kg)
- Gross weight: 500 lb (227 kg)
- Fuel capacity: 5 U.S. gallons (19 L; 4.2 imp gal)
- Powerplant: 1 × Rotax 277 single cylinder, two-stroke aircraft engine, 28 hp (21 kW)
Performance
- Maximum speed: 63 mph (101 km/h; 55 kn)
- Cruise speed: 55 mph (48 kn; 89 km/h)
- Stall speed: 22 mph (19 kn; 35 km/h)
- Service ceiling: 10,000 ft (3,048 m)
- G limits: +3/-2
- Maximum glide ratio: 9:1
- Rate of climb: 700 ft/min (3.6 m/s)
