The Samba XXL is based on successful plane UFM-10 Samba. Excellent flight characteristics were preserved while the space for pilots was extended. That is why Samba XXL is ideal for travelling, training and towing sail planes. SAMBA XXL – brief technical description: The ultra-light plane Samba XXL is a double-seat, single-engine, self-carrying low-wing aeroplane with crew members sitting one next to each other. It is all-composite. The fuselage is made mainly of carbon laminate with local sandwich construction. The wing is of sandwich construction while the flanges are of carbon rowing. The wing is equipped with a lifting flap with a slot. Positions of electrically adjustable flaps are 20° for take-off and 45° for land. The tail surfaces are of classic layout. The carriage is three-wheel with controlled front wheel and braked main wheels. The main carriage legs consist of a laminate spring. Integrated fuel tanks (2 x 50 litres) are located in the wing leading edge. The plane may be equipped with a towing device for sail planes towing with maximal climbing weight of 650 kg. The Samba XXL may be equipped with removable wing extensions. 2009 Price: 50000 EURO
The UTAIS Ornithopter No.1, which “flew” in 2006 was designed by the University of Toronto. The light No.1 used a small motor to power its flapping wings. Realizing that a motor wasn’t enough to flap it off the ground, the designers also fitted the airplane with a jet engine booster to launch it into the air. The University claimed that most of the thrust was coming from the wings.
When the No.1 did its first test flight, it jumped off the runway for 14 seconds after the jet booster activated, traveled awkwardly for a third of a kilometer, nosed down, and crashed. The University claimed the test was a success.
Designed by three engineers from the University of Pretoria, Exulan I is inspired by the shape of albatrosses and pteranodons.
The 1989 Exulans (named after the scientific name for albatros) used some wingtip pivot shift for pitch control, in combination with elevons to overcome the inherent inefficiency of elevons for pitch alone. It was tested successfuly but no commercial version was released.
Designer Joachim Huyssens and his team were working on a second prototype since 2004.
Wing area: 12 m² Wing span: 12 m Length: 3 m Minimum pilot weight: 65 kg Maximum pilot weight: 150 kg Minimum speed: 150 km/h Maximum speed: 40 km/h
The T-1 was a 1936 tailless experimental student project under the guidance of Prof John D Akerman. A single place, open cockpit, low wing monoplane, it was powered by a 55hp Jacobs engine and registered NX14880.
Elmer, George and John Underwood of Stettler, Alberta set to work inventing a flying of their own. The result was a craft with elliptically shaped wings. The Flying Wing was composed of long strips of fir and wire that were covered with cloth. Above the wing was a large fin, with a rudder at the back and an elevator attached to the tail. Under the large wing was a platform where the pilot sat. Motorcycle wheels were placed under the platform and bicycle wheels placed on each wing to hold it steady for take-offs and landings.
The platform also contained a place to house the motorcycle motor once they were able to afford one. In the meantime, the Underwoods displayed their creation at Stettler’s exhibition in July 1907, and tested the machine on their farm.
Tying the aircraft to a fencepost, the brothers placed sacks of wheat on the platform to replicate the weight of a pilot, and launched the plane like a kite. The test went well, and for the next trial, John took the place of the wheat to “fly” the machine for 15 minutes. Their enterprise was then put away until the next year, when the Underwoods finally obtained their motorcycle engine.
Attached to the front of the wing was a large bamboo and canvas propeller, powered by the motorcycle motor. Unfortunately, the brothers found that the engine was too small to get the craft airborne, so they hitched the plane to the fence post once again, using it like a kite, until the Flying Wing was destroyed one day by high winds. Their effort was eventually abandoned, since they lacked the resources to continue.
The Super Pelican is a Canadian design built by Ultravia Aero, Repentigny, Quebec. Being similar in appearance to the Piper Cub it is a high wing taildragger monoplane with a semi-enclosed cabin/fuselage powered by 35hp, Global engine. A conventional 3 axis control microlight of aircraft tube and dacron cover. Engines suitable for the Super Pelican include the Global flat twin four-stroke, 35 hp at 3200 rpm, the three cylinder Konig radial, 25 hp at 4200 rpm, the four cylinder Konig radial, 28 bp at 4200 rpm, or Rotax 277 or 377.
Engine: Global 2 cyl 4 stroke (1039cc), 35 hp Empty wt: 250 lb (113 kg) Max wt: 525 lb (238 kg) Wing span: 35 ft (10.67m) Max cruise: 65 mph (101kph) Stall: 27.5 mph ROC: 950 fpm TO dist 50 ft: 250 ft Seats: 1 Range: 422 km
Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fully flying rudder; roll control by 40% span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile double surface. Undercarriage has three wheels in tail dragger formation; axle Flex suspension on main wheels. Push right go right tailwheel steering connected to yaw control. Optional brakes on main wheels. Aluminium tube framework with glass fibre nose and fabric covering, partially enclosed (total enclosure optional). Engine mounted below wing driving tractor propeller. Covering of framework and wing is Dacron. Ribs made from foam-¬aluminium composite. Aircraft grade aluminium used for structural components. AN hardware.
Ultravia’s publicity material describes Le Pelican as ‘a new ultralight respectful of aircraft tradition’ and is powered by a four stroke twin¬-cylinder Briggs & Stratton engine. Designer Jean Rene Lepage, the Canadian engineer who developed the aircraft over a period of three years, realised that the four stroke was fairly heavy for its rated horsepower and therefore designed the aircraft with long wings and a relatively short nose. Le Pelican is basically a tube and Dacron machine, with D cell wings braced by a single strut and using composite¬ construction ribs made from foam and alumi¬nium alloy. The entire structure was designed in accordance with FAR Part 23, the first aircraft taking to the air on 31 May 1982.
The prototype used spoilers for roll control, though ailerons are now standard, as is a steerable tailwheel (also absent from the prototype). Doors have now been developed to make the cockpit fully enclosed if desired. For those wanting more power, Onan engines of 20 or 22 hp are offered In this form the aircraft was introduced at C$5800 in kit form, the first machines being delivered in February 1983, though this price rose to C$6500. 2009 Price: 5500 US$. Claimed construction and rigging times respectively are 150h and 30 min.
The Pelican was sold in kit form by Ultravia in 1984. It is an aircraft of traditional configuration with a taildragger landing gear and steerable tailwheel. The aircraft was originally fitted with a Global engine and aluminum cowling. The fuselage and tail unit are built with aluminum tubes covered with doped fabric. The wing structure consists of an aluminum D-cell spar on which the styrofoam ribs are mounted. The wings are also covered with doped fabric. Wings are hung to the fuselage with a single strut. All these characteristics combine to give an aerodynamically clean wing with a 12-to-1 glide ratio.
Le Pelican has been compared with the Aeronca C-2, with earlier models being po¬wered by horizontally opposed 4-stroke en¬gines. The strut braced high-wing monoplane is built of aluminium tube gussett rivetted and dacron covered. The engine cowling is one piece fibreglass and the cockpit has remov¬able doors for summer flying.
The Pelican is powered by a Gobal engine. This is the original engine that came with this airframe kit in 1984. The Global is a 4-stroke, 2-cylinder engine based on the Volkswagen flat four, air-cooled engine, except that this one has 2 cylinders instead of four. For this reason, it is often referred to as a half-VW engine. However, the castings are especially designed for aircraft use. This engine is very fuel efficient and burns only 1 gallon of autogas per hour. It is also more reliable than 2-strokes. It is free-air cooled and the oil circulates through an oil cooler located below the fuselage. This engine is devoid of all the troublesome components such as a cooling fan, radiator, hoses, thermostat and other hardware associated with liquid-cooling systems; making it more reliable and less hassle to maintain. The 58 X 24 inch wood propeller is bolted directly to the solid forged crankshaft. This eliminates the potential problems of reduction drives with their added mechanical complexity and heavier weight. The Global develops 35 hp @ 3250 RPM and has plenty of torque for a direct-drive prop. Ignition is by a magneto. This eliminates the need for a battery and alternator and allows for a very simple and reliable electrical system. The Global is started by hand propping; another simple and reliable system that never breaks down. This engine is surprisingly light for a 4-stroke; it weighs only 76 lbs ready-to-run.
Engine: Global, 35 hp @ 3250 RPM Span: 35 ft Length: 15 ft Height: 6.5 ft Wing area: 136 ft.sq Max wing loading: 3.86 lbs.sq.ft Empty weight: 113 kg / 250 lbs MTOW Weight: 238 kg / 525 lbs Useful load: 275 lbs Cruise speed: 60-70 mph Max speed: 80 mph Stall speed: 23 kt / 27 mph / 43 kmh Vne: 78 kt / 90 mph / 145 kmh Max climb rate: 900 ft/min / 5 m/s Fuel capacity: 5 USG Fuel burn: 1 to 1.2 gal.hr Max range: 300 miles Glide Ratio: 12:1 Takeoff distance: 50 ft Landing roll: 100 ft Load factors at 525 lbs: +4 -2 G’s Limit, +6 -3 G’s Ultimate
Engine: Briggs & Stratton, 18 hp at 3600 rpm Prop¬eller diameter 43 inch, 1.09m No reduction Power per unit area 0.13hp/sq.ft, 1.4hp/ sq.m Fuel capacity 2.5 US gal, 2.1 Imp gal, 9.5 litre Empty weight 210lb, 95kg Max take off weight 450lb, 204kg Payload 240lb, 109 kg Max wing loading 3.21 lb/sq.ft, 15.7 kg/sq.m Max power loading 25.0lb/hp, 11.3kg/hp Load factors +4.4, 2.2 design; +6.6, 3.3 ulti¬mate Max level speed 60 mph, 97 kph Never exceed speed 85 mph, 137 kph Max cruising speed 55 mph, 88 kph Economic cruising speed 50 mph, 80 kph Length overall 14.0 ft, 4.27 m Height overall 6.0ft, 1.83m Wing span 37.0ft, 11.28m Constant chord 3.8ft, 1.17m Dihedral 3 deg Sweepback 0 deg Tailplane span 8.0ft, 2.44m Fin height 3.8ft, 1.14m Total wing area 140 sq.ft, 13.0 sq.m Wing aspect ratio 9.8/1 Wheel track 6.0 ft, 1.83 m Wheelbase 11.0 ft, 3.35m Tailwheel diameter overall 4 inch, 10 cm Main wheels diameter overall 20 inch, 51 cm Stalling speed 26 mph, 42 kph Max climb rate at sea level 500 ft/min, 2.5 m/s Min sink rate 250 ft/min at 30 mph, 1.3 in/s at 48 kph Best glide ratio with power off 13/1 at 35 mph, 56kph Take off distance 150ft, 45m Service ceiling 12,500 ft, 3810 m Range at average cruising speed 104 mile, 167 km
Designed by Jean-Rene Lapage, the Canadian designed and built Club first flew in May 1985 and has since entered production at around six a month. The de luxe version of the Club is powered by a HAPI Magnum 75 hp engine.
The Pelican ‘Club’ GS has a composite fuselage has two undercarriage positions moulded in and it is possible to change from tricycle to taildragger configuration in about one hour. This arrangement also makes it easy to fit floats. Dual controls are standard and differential brakes can be fitted. The wings, tailplane and rudder can be demounted in about half an hour so that you can take the ‘Club’ home and hangar it in the lounge.
The fully comprehensive airframe kit contains a 350 page instruction manual, composite fuselage halves factory joined, wing ‘D’ cells factory jigged and all components to complete aircraft to painting stage. Approximate time required is 200 to 250 hours.
The Club VS can be up-graded to S or GS version
The Pelican Sport 450 is a two place single-engine, high wing airplane of conventional configuration consisting of a composite fuselage and metal wings. It is equipped with a fixed tricycle landing gear.
Pelican 450 Engine: Rotax 912, 80 hp Wing span: 10 m Wing area: 11.16 sq.m MAUW: 450 kg Empty weight: 280 kg Fuel capacity: 57 lt Max speed: 254 kph Cruise speed: 195 kph Minimum speed: 65 kph Climb rate: 6 m/s Fuel consumption: 11.3 lt/hr Certification: Canada Seats: 2 Price (1998): $49,995 Kit price (1998): $16,450
Pelican Club GS Engine: Rotax 582, 65 hp Height: 7.6 ft Length: 19.5 ft Wing Span: 34.4 ft Wing Area: 158 sq. ft Empty Weight: 500 lbs Gross Weight: 1050 lbs Fuel Capacity: 22 US gal Top Speed: 115 mph Cruise: 100 mph Range: 500 sm Stall: 33 mph Rate of Climb: 800 fpm Take Off Distance: 300 ft Landing Distance: 425 ft Service Ceiling: 15,000 ft Seats: 2 Landing Gear type: Trigear or Taildragger Kit Cost 2009: $12,500 US
Club GS 912 Engine: Rotax 912, 80 hp MAUW: 1200 lb
Pelican PL Engine: Rotax 912, 80 hp Height: 8.1 ft Length: 19.8 ft Wing Span: 29.5 ft Wing Area: 108 sq. ft Aspect Ratio: 8 Cabin Width: 40 – 46in Headroom: 41 in Seats: 2 Landing Gear: Trigear or Taildragger G Loading: +4, -2 Empty Weight: 750 lbs Gross Weight: 1400 lbs Baggage Capacity: 75 lbs Fuel Capacity: 26 US gal Top Speed: 142 mph 75% Cruise: 115 mph 65% Cruise: 110 mph at 6500 ft Range: 920 sm Stall: 37 mph Rate of Climb: 1000 fpm Take Off Distance: 650 ft Landing Distance: 550 ft Service Ceiling: 16,000 ft Kit Cost 2009: $16,000 US
Pelican PL Engine: Rotax 914, 115 hp Height: 8.1 ft Length: 19.8 ft Wing Span: 29.5 ft Wing Area: 108 sq. ft Aspect Ratio: 8 Cabin Width: 40 – 46in Headroom: 41 in Seats: 2 Landing Gear: Trigear or Taildragger G Loading: +4, -2 Empty Weight: 800 lbs Gross Weight: 1400 lbs Baggage Capacity: 75 lbs Fuel Capacity: 26 US gal Top Speed: 142 mph 75% Cruise: 140 mph 65% Cruise: 130 mph at 12500 ft Range: 920 sm Stall: 38 mph Rate of Climb: 1800 fpm Take Off Distance: 400 ft Landing Distance: 500 ft Service Ceiling: 20,000 ft Kit Cost 2009: $16,000 US
Pelican PL Engine: Rotax Wing span: 9 m Wing area: 9.94 sq.m MAUW: 635 kg Empty weight: 340 kg Fuel capacity: 98 lt Max speed: 241 kph Cruise speed: 233 kph Minimum speed: 71 kph Climb rate: 9 m/s Seats: 2 Kit price (1998): $16,600
Club S Engine: Rotax 582, 65 hp Speed max: 115 mph Cruise: 100 mph Range: 500 sm Stall: 33 mph ROC: 800 fpm Take-off dist: 300 ft Landing dist: 425 ft Service ceiling: 15,000 ft Fuel cap: 22 USG Weight empty: 500 lbs Gross: 1050 lbs Height: 7.6 ft Length: 19.5 ft Wing span: 34.4 ft Wing area: 158 sq.ft Seats: 2 Landing gear: nose or tail wheel
Club VS Engine: Rotax 503, 52 hp Speed max: 100 mph Cruise: 80 mph Range: 290 sm Stall: 35 mph ROC: 600 fpm Take-off dist: 300 ft Landing dist: 500 ft Service ceiling: 13,000 ft Fuel cap: 11 USG Weight empty: 450 lb Gross: 950 lb Height: 7.6 ft Length: 19.5 ft Wing span: 34.4 ft Wing area: 158 sq.ft Seats: 2 Landing gear: tail wheel
Pelican Sport 450 S Stall: 34 kt / 39 mph / 63 kmh Cruise: 111 kt / 127 mph / 205 kmh VNE: 123 kt / 142 mph / 228 kmh Empty Weight: 280 kg / 617 lbs MTOW Weight: 523 kg / 1153 lbs Climb Ratio: 1400 ft/min / 7,6 m/s Take-off distance (50ft obstacle): 490 ft / 150 m
US Aviation Cloud Dancer is a single seat low wing monoplane with a V tail; power comes from a Rotax 277 engine. Centre mounted joy stick, rudder pedals, simultaneous spoilers, tail wheel steerable through rudder pedals.
All Aero 