Thor T/A

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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[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]

  1. ^ 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
  2. ^ a b c d Virtual Ultralight Museum (n.d.). "Thor T/A". Retrieved 2 January 2012. 

External links[edit]