Thor T/A
{{Short description|Canadian ultralight aircraft}}
{{Use dmy dates|date=January 2022}}
{{Use Canadian English|date=January 2022}}
| {{Infobox aircraft begin
| name=T/A | image= | caption= }}{{Infobox aircraft type | type=Ultralight aircraft | national origin=Canada | manufacturer=Thor Air | designer=Thorsten B. Strenger (or possibly Gunter Webster) | first flight= | introduced=1985 | retired= | status=Production completed | primary user= | more users= | produced= | number built= | developed from= | variants with their own articles= }} |
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.Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page E-41. Cybair Limited Publishing, 2001. {{ISBN|0-9680628-1-4}}{{Cite web|url = http://virtualultralightmuseum.com/t.htm#thor|title = Thor T/A |accessdate = 2 January 2012|last = Virtual Ultralight Museum|archiveurl = https://web.archive.org/web/20150507191309/http://virtualultralightmuseum.com/t.htm|archivedate =7 May 2015}}
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 {{convert|254|lb|kg|0|abbr=on}}. The aircraft has a standard empty weight of {{convert|238|lb|kg|0|abbr=on}}. It features a strut-braced high-wing, a single-seat, open cockpit, conventional landing gear and a single engine in tractor configuration.
The aircraft is made from bolted-together aluminum tubing, with its flying surfaces covered in Dacron sailcloth. Its 80% double-surface {{convert|32.3|ft|m|1|abbr=on}} 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.
Variants
;T/A
:Initial design, powered by a {{convert|28|hp|kW|0|abbr=on}} Rotax 277 single cylinder, two-stroke powerplant.
;1-A{{Anchor|1-A}}
:Up-engined model, powered by a {{convert|40|hp|kW|0|abbr=on}} Rotax 447 twin cylinder, two-stroke powerplant.
;Two-seater
:Similar to the single-seat models but with a second seat for dual instruction.
Specifications (T/A)
{{Aircraft specs
|ref=Cliche and the Virtual Ultralight Museum
|prime units?=imp
|genhide=
|crew=one
|capacity=
|length m=
|length ft=13.8
|length in=
|length note=
|span m=
|span ft=32
|span in=4
|span note=
|height m=
|height ft=7
|height in=8
|height note=
|wing area sqm=
|wing area sqft=167
|wing area note=
|aspect ratio=
|airfoil=
|empty weight kg=
|empty weight lb=238
|empty weight note=
|gross weight kg=
|gross weight lb=500
|gross weight note=
|fuel capacity={{convert|5|u.s.gal}}
|more general=
|eng1 number=1
|eng1 name=Rotax 277
|eng1 type=single cylinder, two-stroke aircraft engine
|eng1 kw=
|eng1 hp=28
|prop blade number=
|prop name=
|prop dia m=
|prop dia ft=
|prop dia in=
|prop note=
|perfhide=
|max speed kmh=
|max speed mph=63
|max speed kts=
|max speed note=
|cruise speed kmh=
|cruise speed mph=55
|cruise speed kts=
|cruise speed note=
|stall speed kmh=
|stall speed mph=22
|stall speed kts=
|stall speed note=
|never exceed speed kmh=
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|range km=
|range miles=
|range nmi=
|range note=
|endurance=
|ceiling m=
|ceiling ft=10000
|ceiling note=
|g limits=+3/-2
|roll rate=
|glide ratio=9:1
|climb rate ms=
|climb rate ftmin=700
|climb rate note=
|time to altitude=
|sink rate ms=
|sink rate ftmin=
|sink rate note=
|lift to drag=
|wing loading kg/m2=
|wing loading lb/sqft=
|wing loading note=
|power/mass=
|thrust/weight=
|more performance=
|avionics=
}}
{{aircontent
|see also=
|related=
|similar aircraft=
|lists=
}}