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International Ultralight Wanderer


The Wanderer was a single-seat single-engined high-wing monoplane with conventional three-axis control. Wing has swept back leading edge, swept forward trailing edge and tapering chord; conventional 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. Cantilever wing; wing profile; double surface. Undercarriage has three wheels in taildragger formation; suspension on tailwheel; suspension on main wheels. Tailwheel steering. No brakes. Steel tube fuselage, totally enclosed. Engine mounted above wing driving pusher propeller.


The Wanderer is a soaring machine and appeared in 1982.


The test pilot, George Worthington, had a miraculous escape when a wing broke during a spin of the prototype of the Wanderer in August 1982. On the 10 September 1982 he was killed in the second prototype after a similar break in the wing. The aircraft may not go into series production.

Engine Yamaha KT-100S, 15hp at 10,000rpm.
Power per unit area 0.11hp/sq.ft, 1.21 hp/sq.m.
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 17.0 ft, 5.18 m.
Height overall 3.6ft, 1.08m.
Wing span 35.6ft, 10.82m.
Total wing area 133 sq.ft, 12.4sq.m.
Wing aspect ratio 9.5/1.
Empty weight 190 lb, 86kg.
Max take-off weight 480 lb, 218kg.
Payload 270 lb, 132kg.
Max wing loading 3.6 lb/sq.ft, 17.6 kg/sq.m.
Max pow-er loading 32.0 lb/hp, 14.5 kg/hp.
Load factors; +4.6, -4.6 ultimate.
Max level speed 75 mph, 121 kph.
Max cruising speed 60 mph, 97kph.
Stalling speed 25mph, 40kph.
Max climb rate at sea level 300 ft/min, 1.5 m/s.
Best glide ratio with power off 17/1 at 40 mph, 64 kph.
Take-off distance 200 ft, 60 m.
Land-ing distance 300 ft, 90 m.
Range at average cruising speed 240 mile, 386 km.

 


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