ATEC 212 Solo

{{Infobox aircraft | name = 212 Solo | logo = | logo_size = | image = | alt = | caption = | long_caption = | other_names = | aircraft_type = [[Ultralight aircraft]] | aim = | outcome = | related = | national_origin = [[Czech Republic]] | manufacturer = [[ATEC v.o.s.]] | design_group = | designer = | builder = | issuer = | status = In production | owners = | primary_user = | more_users = | service = | major_applications = | proposals = | prototypes = | number_built = | construction_number = | civil_registration = | military_serial = | radio_code = | requirement = | aircraft_carried = | flights = | total_hours = | total_distance = | construction_date = | introduction = | retired = | first_flight = | initiated = | in_service = | last_flight = | expected = | developed_from = | variants = | developed_into = | preservation = | fate = | predecessors = | successors = | concluded = }} The '''ATEC 212 Solo''' is a [[Czech Republic|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.<ref name="WDLA11">Bayerl, Robby; Martin Berkemeier; et al: ''World Directory of Leisure Aviation 2011-12'', page 28. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X</ref><ref name="WDLA15">Tacke, Willi; Marino Boric; et al: ''World Directory of Light Aviation 2015-16'', page 29. Flying Pages Europe SARL, 2015. {{ISSN|1368-485X}}</ref>

==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]].<ref name="WDLA11" /><ref name="WDLA15"/>

The 212 Solo is made from [[carbon fibre]] and was derived from the [[ATEC 321 Faeta]] and [[ATEC 122 Zephyr 2000]] designs. Its {{convert|7.48|m|ft|1|abbr=on}} span wing employs an SM701 [[airfoil]] and [[Flap (aircraft)|slotted flaps]]. Standard engines available are the {{convert|64|hp|kW|0|abbr=on}} [[Rotax 582]] [[two-stroke]] and the {{convert|80|hp|kW|0|abbr=on}} [[Rotax 912UL]] [[four-stroke]] powerplant.<ref name="WDLA11" /><ref name="WDLA15"/>

==Specifications (212 Solo) == {{Aircraft specs |ref=Bayerl<ref name="WDLA11" /><ref name="WDLA15"/> |prime units?=met  |genhide=

|crew=one |capacity= |length m= |length ft= |length in= |length note= |span m=7.48 |span ft= |span in= |span note= |height m= |height ft= |height in= |height note= |wing area sqm=7.27 |wing area sqft= |wing area note= |aspect ratio= |airfoil= |empty weight kg=200 |empty weight lb= |empty weight note= |gross weight kg=315 |gross weight lb= |gross weight note= |fuel capacity={{convert|50|L}} |more general=  |eng1 number=1 |eng1 name=[[Rotax 582]] |eng1 type=twin cylinder, liquid-cooled, [[two stroke]] |eng1 kw=48 |eng1 hp=

|perfhide=

|max speed kmh=250 |max speed mph= |max speed kts= |max speed note= |cruise speed kmh=220 |cruise speed mph= |cruise speed kts= |cruise speed note= |stall speed kmh=65 |stall speed mph= |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= |ceiling note= |g limits= |roll rate= |glide ratio= |climb rate ms=7 |climb rate ftmin= |climb rate note= |time to altitude= |sink rate ms= |sink rate ftmin= |sink rate note= |lift to drag= |wing loading kg/m2=43.32 |wing loading lb/sqft= |wing loading note= |power/mass= |thrust/weight= |more performance= |avionics= }}

==References== {{reflist}}

==External links== *{{Official website|https://www.atecaircraft.eu/en/planes/atec-212-solo}} {{ATEC aircraft}}

[[Category:2000s Czech ultralight aircraft]] [[Category:Single-engined tractor aircraft]] [[Category:ATEC aircraft]]