Manufactured by Fabrications Aeronoutiques ATESMA company (FAA). All hardware and parts are aviation certified. Assembly time 10 min. Car toppable.
Engine: 50hp Fuji Robin EC44PM with Mecoworms 2.5/1 reduction.
Wing area: 215 sq.ft.
Empty weight (wing plus trike unit) 251 lb.
Max payload 397 lb.
Max level speed at gross weight 49 mph.
Max cruising speed 43 mph.
Stall speed 19 mph.
Seats: 2.
The 1909 Cluzan biplane was designed and built by Cluzan in France.
Span: 33’9″
The design of the EC-2 all wood low wing single seat monoplane was started by Eric Clutton in 1969. It was designed to be as simple to build as the FRED, but with aerobatic capability.
The prototype, PFA.1361 was started in Stoke-on-Trent, to be powered by a belt-reduced VW1500.
Wingspan: 23.04 ft
Designed by Eric Clutton of Stoke-on-Trent in conjuction with E.Sherry during 1957 to 1963. FRED stands for “Flying Runabout, Experimental Design,” but the design is now far from experimental, says its designer – Eric Clutton. A parasol-type single-seater, FRED has folding wings for road-towing. It has steel spring shocks for rough-field operations. Volkswagon powered.
Clutton started building the first, G-ASZY PFA.1311 cn EC/ES/1A in 1957 at Stoke-on-Trent, finished at Meir and first flown from there on 3 November 1963 with a modified Triumph 5T as FRED Series 1. It was re-engined with a Scott A.2S in 1965 to demonstrate the wide range of engines it can take. It was further re-engined in 1966 with a Lawrence radial as FRED Series II.
From 1968 it was used as a testbed for the Clutton belt-reduced VW of various sizes and drives, eventually with an EC/VW1500.
Badly damaged at Meir in 1974, it was rebuilt and flown again in mid-1975 in WW1 German markings including lozenge markings.
Engine: VW, 65 hp.
HP range: 55-65.
Height: 6 ft.
Length: 16 ft.
Wing span: 22.5 ft.
Wing area: 110 sq.ft.
Speed max: 85 mph.
Cruise: 70 mph.
Stall: 29 mph.
ROC: 500 fpm.
Take-off dist: 900 ft.
Landing dist: 450 ft.
Fuel cap: 14 USG.
Weight empty: 550 lbs.
Gross: 800 lbs.
Seats: 1.
Landing gear: tail wheel.
The Club ULM Rotor Ptenets-2 (Russian: Птенец-2, English: Chick or Fledgling) is a Russian ultralight aircraft, designed and produced by Club ULM Rotor of Kumertau, Bashkortostan.
The aircraft was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a strut-braced high-wing, a two-seats-in-side-by-side configuration enclosed cockpit, fixed tricycle landing gear and a single engine in pusher configuration.
The aircraft is made from aluminum tubing, with its flying surfaces covered in Dacron sailcloth. The fuselage is made from fibreglass. Its 10.2 m (33.5 ft) span wing has an area of 12.7 m2 (137 sq ft). The tail is supported by four tubes that allow space for the pusher propeller. Standard engines available are the 50 hp (37 kW) Rotax 503 and 64 hp (48 kW) Rotax 582 two-strokes and the 60 hp (45 kW) HKS 700E four-stroke powerplant.
The aircraft was supplied as a complete ready-to-fly-aircraft for €21,000 in 2011.
Ptenets-2
Engine: 1 × Rotax 582, 48 kW (64 hp)
Propeller: 4-bladed composite
Wingspan: 10.2 m (33 ft 6 in)
Wing area: 12.7 m2 (137 sq ft)
Empty weight: 220 kg (485 lb)
Gross weight: 450 kg (992 lb)
Fuel capacity: 55 litres (12 imp gal; 15 US gal)
Maximum speed: 160 km/h (99 mph; 86 kn)
Cruise speed: 120 km/h (75 mph; 65 kn)
Stall speed: 65 km/h (40 mph; 35 kn)
Rate of climb: 4 m/s (790 ft/min)
Capacity: one passenger
Crew: one
The Cadi was created by an ex-employee of Aviation Normand Dube. Metal covered, the Cadi can be ultralight or experimental.
Engine: Rotax 912, 80 hp
Wing span: 9.74 m
Wing area: 16 sq.m
MAUW: 544 kg
Empty weight: 274 kg
Fuel capacity: 90 lt
Seats: 2
Max speed: 160 kph
Cruise speed: 142 kph
Climb rate: 4.5 m/s
Fuel consumption: 12 lt/hr
Certification: Canada
Price (1998): Can$50,000
Kit price (1998): Can$15,000
The Jenny is a three-quarter scale replica of the famous Curtiss JN4D Jenny Trainer. Although this ultralight version has a rear cockpit it is there purely for aesthetics and is non-functional. The airframe is gussett riveted aluminium tubing covered in a doped dacron finish. Centre mounted joy stick, rudder pedals.
I flew one many years ago here in Australia. A delightful short range aircraft. The ailerons do not exist. What there is are spoilers on the tops of the upper wings and controlled by a linen cord that pulled them up thus spoiling the air flow. Spoiler up and the lift on the other side raised that wing thus a turn. Real STOL take-off and landing. Mt first experience with a two stroke. Love to own this Curtiss Jenny! Now I can say that I have flown both a Curtiss Jenny and a Boeing! (A Stearman).
David Prossor
Engine: Cuyuna ULII-02 (429 cc) 35 hp.
Prop: 198cm.
Static thrust: 296 lbs.
Empty wt: 248 lbs.
Wing span: 28’4”.
Wing area: 186 sq.ft.
Height: 7’6”.
Length: 17’.
Fuel cap; 5 USG.
Construction: Alumnium, Dacron.
Max wt: 500 lbs.
Stall: 21 mph.
Max speed: 62 mph.
Vne: 69 mph.
Econ cruise speed: 45 kts.
Climb rate: 1000 fpm @ 40 mph.
Design limit: +4, -2g.
Glide ratio: 5.5-1.
Wing loading: 2.69 lbs/sq.ft.
Power loading: 14.29 lbs/hp.
Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading edge, swept forward trailing edge and tapering chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by one third 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 tricycle formation; steel ¬spring suspension on nosewheel and steel spring suspension on main wheels. Nosewheel steering connected to yaw control. Brake on nosewheel. Aluminium tube 6063-T6 framework, without pod. Engine mounted at wing height driving tractor propeller. Wing spar strut braced to the cage, ribs made of foam and unidirectional glass fibre and epoxy.
Cloudbuster Ultralights Cloudbuster Article
The Cloudbuster made its appearance in 1981. It is fitted with a rigid wing with duralumin tube spars and ribs of high density polyurethane foam, reinforced by a layer of unidirectional glass fibre and epoxy. Wing and tail surface covering is 1.7-ounce Dacron. The leading edge is vinyl and the trailing edge is aluminium sheet bonded to the back of the spars with epoxy. At the wing tips there are semi elliptic saumons and the ailerons are hinged from a false spar.
Undecarriage was tricycle with coil-spring independent suspension and a steerable nosewheel. The main wheels are 20”, and the nose wheel is 16”. A hand-operated bicycle-type brake is fitted to the nosewheel.
The prototype Cloudbuster was equipped with a Skylark Ultra 342 motor and a 2.0 reduction gear turning a two-blade Woody’s prop measuring 58×27”, which was dropped on the initial production models in favour of the Zenoah G25B developing 20 hp at 6500 rpm. Two other options were offered for this machine; the Cuyuna 215R (20hp at 5500 rpm) with a 2.5/1 reduction drive, or the Cuyuna 430R (30 hp at 5500 rpm).
Transport by road requires a trailer, the two half wings and the horizontal tail surfaces being de mounted.
The Cloudbuster is sold as a kit at various stages of finish with or without motor at the choice of the customer. The price was dependent on the kit chosen.
Engine displacement 430 Cuyuna or 342 Ultra (rated 35 and 30 hp).
Wingspan 36 ft.
Wing area 150 sq.ft.
Overall length 15 ft 6 in
Engine: Zenoah G25B, 20 hp at 6500 rpm.
Belt reduction, ratio 2.5/1.
Power per unit area 0.13 hp/sq.ft, 1.40 hp/sq.m.
Fuel capacity 3.5 US gal, 2.9 Imp gal, 13 litre.
Length overall 15.6 ft, 4.72 m.
Height overall 7.4 ft, 2.23 m.
Wing span 37 ft, 11.28 m.
Mean chord 4.1ft, 1.24 m.
Total wing area l53sq.ft, 14.2 sq.m.
Wing aspect ratio 8.9/1.
Nosewheel diameter overall 16 inch, 40 cm.
Main wheels diameter overall 20 inch, 50 cm.
Empty weight 248 lb, 112kg.
Max take off weight 532 lb, 241kg.
Payload 284 lb, 129kg.
Max wing loading 3.48 lb/sq.ft, 17.0kg/sq.m.
Max power loading 26.6 lb/hp, 12.0kg/hp.
Load factors; +4.5, 2.25 ultimate.
Max level speed 60 mph, 97 kph.
Never exceed speed 65 mph, 105kph.
Economic cruising speed 45 mph, 72 kph.
Stalling speed 25 mph, 40 kph.
Max climb rate at sea level 650 ft/min, 3.3 m/s.
Min sink rate 260 ft/min, 1.3 m/s.
Best glide ratio with power off 13/1 at 32 mph, 51 kph.
Take off distance 80 ft, 25 m.
Landing distance 100 ft, 30 m.
Service ceiling 10,000ft, 3050 m.
Range at average cruising speed 135 mile, 217 km.
A gyrocopter begun on 3 August 1995. The gyro has rotors by Jack Allen, a redrive made by C.M.A. in Christchurch, and rotor head built by Neil Hintz. The joystick, nose wheel, wheels, pedals and aluminium were purchased from Wayne Morgan in Australia. No plans were used, but the machine was built from photos of an Air Command. Test flown in February 1996 by Gary Belton. First registered ZK-RAX, to E.J.Clince, Stratford, New Zealand, on 24 December 1996.
Engine: Subaru EA81, 85 hp.
Rotor dia: 24 ft.
Prop: Warp Drive 68 in.
Cruise: 60 kt.
Max speed: 80 kt.
The 1910 Clerget monoplane was designed and built by Pierre Clerget in France.
Span: 36’1″
Length: 49’11”
