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Scheibe Uli II

Tandem two-seat single-engined high-wing monoplane with conventional three-axis control. Wing has unswept leading and trailing edges and constant chord; conventional tail. Pitch control by fully flying tail; yaw control by fully flying rudder; roll control by half-span ailer-ons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables; wing profile double-surface. Steel-tube framework, with optional pod. Engine mounted below wing driving pusher propeller. Wings use two aluminium tubes as spars, with ribs in foam, capped top and bottom with wood; all flying surfaces covered in Ceconite.

This tandem two-seater version of the Uli made its first flights in February 1983 and by 1983 two prototypes had been built, which were undergoing certification. The aircraft is fitted with the four-cylinder Konig 570cc engine and uses either a two-blade or a three-blade design of 51 inch (1.30 m) dia-meter.

Length overall 18.1ft, 5.52m
Wing span 35.4 ft, 10.80 m
Constant chord 4.4 ft, 1.33 m
Sweepback 0 deg
Tailplane span 7.2 ft, 2.20 m
Total wing area 161 sq.ft, 15.0 sq.m
Wing aspect ratio 7.8/1
Wheel track 4.6 ft, 1.40 m
Engine: Konig SD570, 28 hp at 4200 rpm
Propeller diameter 58 inch, 1.47 m. 2-blade
Belt reduction, ratio 1.8/1
Max static thrust 177 lb, 80 kg
Power per unit area 0. 17 hp/sq.ft, 1.9hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre
Empty weight 221 lb, 100kg
Max take-off weight 618 lb, 280kg
Payload 397 lb, 180kg
Max wing loading 3.81 lb/sq.ft, 18.7 kg/sq.m
Max power loading 22.1 lb/hp, 10.0kg/hp
Load factors; +6.0, -3.0 ultimate
Economic cruising speed 37 mph, 60 kph
Stalling speed 28 mph, 45 kph
Best glide ratio with power off: 9/1
Take-off distance 260 ft, 80 m

 

 


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