Designed by Jacques Norman, the fuselage is made from 4130 Chromoly steel and all parts are joined with high quality weldings. Wings are made of lightweight wood with full length I-beams as well as geodesic ribs. The material of choice for the skin is Ceconite 102, known for its resistance and fire retardant properties. One notable feature is the long range wing tank with a 16 gallon fuel capacity, and hydraulic brakes.

The maximum allowed weight in the category “Ultra-light advanced type” is 1058lbs for the Nordic VI-912 and 914. The maximum allowed weight in the experimental category is 1200lbs.

A two seater side-by-side, wheels, floats and skis were available. The landing gear is Titanium. Nordic 6 2009 Price was US$19895.

Nordic II
Length: 19 ft
Height: 5.6 ft
Wingspan: 33.8 ft
Wing area: 154 sq.ft
Weight empty: 600 lbs
Maximum weight: 1058 lbs
Useful load: 438 lbs
Fuel capacity: 16 US
Optional fuel capacity: 20 USG
Maximum speed: 130 mph
Manouvering speed: 70-90 mph
Stall speed at full flaps: 35 mph
Maximum speed with flaps: 70 mph
Crusing speed at 75% power: 85 mph
Maximum climb rate: 600 fpm
Landing distance: 200′ ft
Take-off distance: 150 ft
Operating range: 400 mls
Ceiling: 10 000′ ft
Maximum cross wind: 25 mph
Cabin width: 39 in
Baggage weight: 60 lbs
Seats: 2

Nordic II
Engine: Subaru EA-81, 71 hp
HP range: 71-90
Length: 19 ft
Height: 5.6 ft
Wingspan: 33.8 ft
Wing area: 154 sq.ft
Weight empty: 620 lbs
Gross: 1058 lbs
Speed max: 100 mph
Cruise: 85 mph
Range: 340 sm
Stall: 35 mph
ROC: 600 fpm
Take-off dist: 150 ft
Landing dist: 300 ft
Service ceiling: 10,000 ft
Landing gear: tail wheel

Nordic VI
Engine: Subaru EA-81, 71 hp
HP range: 71-90
Height: 5.5 ft
Length: 19 ft
Wing span: 33 ft
Wing area: 154 sq.ft
Weight empty: 620 lbs
Gross: 1058 lbs
Fuel cap: 10 USG
VNE: 117 kt / 135 mph / 217 kmh
Speed max: 100 mph
Cruise: 90 mph
Range: 360 sm
Stall: 33 kt / 38 mph / 61 kmh
ROC: 500 fpm
Take-off dist: 200 ft
Landing dist: 350 ft
Service ceiling: 10,000 ft
Seats: 2
Landing gear: tail wheel

Nordic VI
Engine: Subaru EA81, 71 hp
Wing span: 10 m
Wing area: 15.5 sq.m
MAUW: 400 kg
Empty weight: 272 kg
Fuel capacity: 37 lt
Max speed: 210 kph
Cruise speed: 145 kph
Minimum speed: 61 kph
Climb rate: 2.5 m/s
Fuel consumption: 9.5 lt/hr
Seats: 2
Plan price (1998): Can$450
Kit price (1998): Can$7,750

Nordic VI-912
Engine: Rotax 912, 82 hp
Length: 20 ft 2 in
Height: 7 ft 1 in
Wing span: 33 ft 6 in ‘
Wing area: 152 sq.ft
Max speed: 110 mph
Weight empty: 586 lbs
Maximum weight: 1058 lbs
Useful load: 472 lbs
Fuel tank capacity: 16 USG
Cruising speed: 103 mph (5000 rpm)
Stall speed at full flaps: 34 mph
Stall speed without flaps: 42 mph
Range: 400 sm
Landing distance: 350 ft
Take-off distance: 250 ft
Ceiling: 10 000 ft
Maximum climb rate: 1100 fpm (solo)
Endurance: 5 hours
Loading limit: +6 / -4 G
Cabin width: 39 in
Baggage weight: 60 lbs
Baggage space: 9 cu.ft
Seats: 2

Nordic VI-914
Engine: Rotax 914, 100 hp
Length: 20.1 ft
Wing span: 29.6 ft
Wing area: 132 sq.ft
Empty weight: 594 lb
Gross weight: 1320 lb
Fuel capacity: 16 USG
Cruise: 110 mph
Stall: 38 mph
Range: 460 sm
Rate of climb: 2200 fpm
Takeoff dist: 150 ft
Landing dist: 300 ft
Cockpit width: 39 in
Landing gear: tailwheel

Nordic VI-914 Turbo
Engine: Rotax 914, 115 hp
Length: 20 ft 2 in
Height: 7 ft 1 in
Weight empty: 594 lbs
Maximum weight: 1058 lbs
Payload: 464 lbs
Fuel capacity: 16 USG
Cruising speed: 110 mph (5000 rpm)
Stall speed at full flaps: 34 mph
Stall speed without flaps: 42 mph
Maximum climb rate: 2200+ fpm (solo)
Landing distance: 350 ft
Take-off distance: 150 ft
Endurance: 4.5 hours / heures
Load limit: +6 / -4 G
Baggage weight: 60 lbs
Baggage space: 9 cu.ft
Seats: 2

Nordic VI-912-SW
Engine: Rotax 912, 80 hp
Length: 20.1 ft
Wing span: 29.6 ft
Wing area: 132 sq.ft
Empty weight: 582 lb
Gross weight: 1232 lb
Fuel capacity: 16 USG
Cruise: 115 mph
Stall: 38 mph
Range: 460 sm
Rate of climb: 1200 fpm
Takeoff dist: 250 ft
Landing dist: 350 ft
Seats: 2
Cockpit width: 39 in
Landing gear: Tailwheel

Designer Bela Nogrady started prototype 01 of the AN 2 in 1982 and it made its first flights in July 1982. The Avionnette had a conventional empennage at first, with quar¬ter span spoilers, after which a V tail was tried with fully flying elevons. This butterfly ¬tail configuration with 110 degrees between the two surfaces was adopted for prototype 02, which made its first flights at the end of April 1983, but the elevons are no longer fully flying, hingeing instead from inclined fixed surfaces, this tail being a NACA 0015 profile.

Production Avionnettes retain the constant ¬chord wing without leading edge sweepback, as used on the first prototype, but will be fitted with ailerons and flaps as tried on 02. With a total surface area of 15.1 sq.ft (1.40sq.m), these flaps have three positions: 15, 30 and 55 degrees. The wing tips now have semi elliptic end plates and the profile used on 01, the Worthmann FX S02 184, set at 6 degrees without washout and with 3 degrees of dihedral, has been replaced by an FX 66S-171, set at 6 degrees incidence with the same dihedral and still without washout.

Production was programmed to get up to six machines a month before the end of 1983. The AN 2 comes as standard with dual controls and a retractable main wheel with wheel well door and drum brake; under development is a tail dragger version with laminated carbon ¬fibre main gear. The wings and tail surfaces are easily de mountable and the AN 2 is trailer transportable.

The standard model comes with a three blade propeller, ground adjustable for pitch.

Side by side two seat single engined mid wing monoplane with conventional three axis con¬trol. Wing has unswept leading and trailing edges, and constant chord; V tail. Pitch/yaw control by elevon; roll control by one third ¬span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing of Worthmann FX66 S 171 profile; double surface. Undercarriage has two wheels in tandem with skid under each wing; rubber suspension on main wheel. Push right go right tailwheel steering connected to yaw control. Brake on main wheel. Glass fibre fuselage totally enclosed. Engine mounted at wing height driving tractor propeller. Carbon fibre wing spar with Kevlar, aluminium ribs, Dacron covering and plastic leading edge.

This microlight offers a maximum level speed of 106 mph (170 kph) take off at 23mph (38kph) and cruise be¬tween 56 and 93 mph (90 150 kph) with 43 hp thrust and a gross weight of 662 lb (300 kg). The AN 2 could be mistaken for a modern motor glider, with its composite construction, glide ratio of 26.4/1 and aspect ratio of almost 12/1.

Engine: Hirth 2701R 53, 43 hp at 6750 rpm
Propeller diameter and pitch: 51 x 45 inch, 1.30 x 1.15 m
V belt reduction ratio: 2.21
Power per unit area 0.28 hp/sq.ft, 3.0hp/sq.m
Fuel capacity 10.6 US gal, 8.8 Imp gal, 40.0 litre
Length overall 21.1 ft, 6.38 m
Height overall 5.1ft, 1.80m
Wing span 42.8ft, 13.00m
Constant chord 3.7 ft, 1.10m
Dihedral 3 degrees
Sweepback 0 degrees
Tailplane span 12.2 ft, 3.70 m
Total wing area 152 sq.ft, 14.1 sq.m
Total aileron area 8.6 sq.ft, 0.80sq.m
Tailplane area 22.8 sq.ft, 2.12 sq.m
Total elevon area 11.6 sq.ft, 1.08 sq.m
Wing aspect ratio 2.1/1
Wheelbase 16.1ft, 4.90m
Tailwheel diameter overall: 6 inch, 16 cm
Main wheels diameter overall 19 inch, 48 cm
Empty weight 2651b, 120kg
Max take off weight 6621b, 300kg
Payload 397 lb, 180 kg
Max wing loading 4.351b/sq.ft, 21.3 kg/sq.m
Max power loading 15.41b/hp, 7.0kg/hp
Load factors; +8.0, 4.0 ultimate
Max level speed 106mph, 170kph
Never exceed speed 117mph, 189kph
Max cruising speed 93mph, 150kph
Economic cruising speed 56mph, 90kph
Stalling speed 23mph, 38 kph
Max climb rate at sea level: 600 ft/min, 3.1 m/s
Min sink rate 138ft/min at 30mph, 0.7 m/s at 48 kph
Best glide ratio with power off: 26.4/1 at 45 mph, 72 kph
Take off distance 193 ft, 59m
Landing distance 213 ft, 65 m
Service ceiling 23,000ft, 7000m
Range at average cruising speed: 497 mile, 800km

The Noble Hardman Snowbird Mk.IV is a 2-seat high-wing microlight aeroplane powered by a single Rotax 532 engine. The Mk.IVs are built by Noble Hardman Aviation Ltd and test flown at the Cardiff-Rhoose Airport in Wales.

Tandem two seat single engined high wing monoplane with conventional three axis con¬trol. Wing has swept back leading edge, unswept trailing edge and tapering chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile NACA 4412 with 2.5 deg washout; 100% double surface. Undercarriage has three wheels in tricycle formation; steel spring suspension on all wheels. Push right go right nosewheel steering connected to yaw control. Brake on nosewheel. Aluminium tube framework partially enclosed. Engine mounted below wing driving tractor prop¬eller.

The Snowbird was a conventional three axis machine with dual controls (including a dual throttle) and tube and Dacron construction. Its wing design uses a quarter chord twin-¬tube main spar with resilient foam D sections and tube aft sections. The ribs are capped with aluminium and all fabric is removable for inspection and maintenance.

A feature of the float kit is that the floats will not be attached rigidly to the aircraft but will be fitted with a suspension system consisting of a front rocker bar and air dampers.

Engine: Robin EC44, 50hp at 6500rpm
Propeller diameter and pitch 62 x 27 inch, 1.57 x 0.69 m
Toothed belt reduction, ratio 2.8/1
Max static thrust 320 lb, 145 kg
Power per unit area 0.28 h p/sq.ft, 3.0hp/sq.m
Fuel capacity main tank 4.8 US gal, 4.0 Imp gal, 18.2 litre
Fuel capacity reserve 1.2 US gal, 1.0 Imp gal, 4.5 litre
Length overall 20.0 ft, 6.10 m
Height overall 7.6ft, 2.32m
Wing span 36.0ft, 10.97m
Chord at root 5.6ft, 1.70m
Chord at tip 4.4ft, 1.35m
Dihedral 2 degrees
Sweepback 3 degrees
Tailplane span 6.6 ft, 2.00 m
Fin height 4.1 ft, 1.25 m
Total wing area 180 sq.ft, 16.7 sq.m
Total aileron area 16.5 sq.ft, 1.53 sq.m
Fin area 12.5 sq.ft, 1.16 sq.m
Rudder area 7.5 sq.ft, 0.70 sq.m
Tailplane area 22.4 sq.ft, 2.08 sq.m
Total elevator area 7.5 sq.ft, 0.70 sq.m
Wing aspect ratio 7.2/1
Wheel track 6.3ft, 1.92 m
Wheelbase 5.2ft, 1.58 m
Nosewheel diameter overall 14 inch, 36 cm
Main wheels diameter overall 16 inch, 41 cm
Optional floats: length 12.0ft, 3.66m, buoyancy 1200 lb, 544kg
Empty weight 300 lb, 136 kg
Max take off weight 696 lb, 316kg
Payload 396 lb, 180 kg
Max wing loading 3.87 lb/sq.ft, 18.9 kg/sq.m
Max power loading 13.9 lb/hp, 6.3 kg/hp
Load factors +6.0, 4.0 design
Max level speed 65 mph, 105 kph
Never exceed speed 80 mph, 129 kph
Stalling speed 28 33 mph, 45 53 kph
Max climb rate at sea level 750 ft/min, 3.8 m/s

The Nexaer LS1, a 2-seat composite airplane that meets Light Sport Aircraft classifications and is being promoted and marketed by Sportplanes.com. The LS1, manufactured by Nexaer in Colorado Springs, Colorado, fetures a 54” wide cockpit, a cruise speed of 120 knots and a useful load in excess of 600 lbs. The prototype of the LS1 was unveiled at AirVenture 2005.
With a moulded carbon fiber composite structure, the Nexaer LS1 features a 4-point harness, and an all-plane parachute.

Standard features include:
No-flap
Tricycle landing gear for easy ground handling
Molded Kevlar® fuel tank (single center-mounted tank)
21-inch-wide seating with slide and tilt adjustment
Cabin heat and vent
Rear baggage compartment for standard cargo
Sporting goods cargo area for skiis, fishing poles, hunting gear, and golf clubs
Passenger-side glove compartment with flip-down tray and 12V power outlet

Standard Edition (SE)
Jabaru 2200 engine (80 hp)
Standard mechanical flight instruments (6-pack)
Standard analog engine gauges
Garmin SL-40 comm radio
Garmin GTX327 digital transponder
Single pilot-side yoke and pedals
Landing light
Navigation lights and strobes

Trainer Edition (TE)
Jabaru 2200 engine (80 hp)
Standard mechanical flight
instruments (6-pack)
Standard analog engine gauges
Garmin SL-30 nav/comm radio
Garmin GTX327 digital transponder
Dual flight controls
Landing light
Navigation lights and strobes
All-plane parachute

Luxury Edition (LE)
Jabaru 3300 engine (120 hp)
Dual electronic flight instrumentation system (EFIS)
Dual GPS
Electronic engine monitor with matching LCD display
Garmin SL-40 comm radio
Garmin GTX330 digital transponder
PSEngineering PCD7100-I stereo intercom with CD/MP3
2-axis digital autopilot
Single pilot-side flight controls
Landing light
Navigation lights and strobes
All-plane parachute
Keychain remote door unlock and open

Length: 23.25 ft.
Height: 7 ft. 10 in.
Wing span: 29.5 ft.
Wing Area: 124 sq. ft.
Cabin Width: 54 in.
Seat width: 21 in.
Max Gross Weight: 1320 lbs.
Empty Weight: 750 lbs.
Fuel Capacity: 27 USgal. (162 lbs.)
Useful Load: 570 lbs.
Design load factor: +4.5/-2.0 g
Power: 80 – 120 hp
Stall speed: 44 knots (51 mph)
Max speed in level flight: 120 knots (138 mph)
Maneuvering speed (VA): 105 knots (121 mph)
Never-exceed speed (VNE): 160 knots (184 mph)
Max rate of climb (sea level): 1500 ft./min
Max rate of climb (10,000 ft.): 700 ft./min
Service ceiling: TBD
Take-off distance (sea level): 350 ft
Take-off distance (10,000 ft): 750 ft
Endurance: 4 hours (with 30 minute reserve)
Range: 550 miles (ave.)