Thor T/A
| T/A | |
|---|---|
| Role | Ultralight aircraft |
| National origin | Canada |
| Manufacturer | Thor Air |
| 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[edit]
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[edit]
- 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)[edit]
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 (89 km/h, 48 kn)
- Stall speed: 22 mph (35 km/h, 19 kn)
- Service ceiling: 10,000 ft (3,000 m)
- g limits: +3/-2
- Maximum glide ratio: 9:1
- Rate of climb: 700 ft/min (3.6 m/s)
References[edit]
- ^ a b c d e f g Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page E-41. Cybair Limited Publishing, 2001. ISBN 0-9680628-1-4
- ^ a b c d Virtual Ultralight Museum. "Thor T/A". Archived from the original on 7 May 2015. Retrieved 2 January 2012.