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AILE sa PX-2000

 

ailepx2000


Single-seat single-engined high-wing mono-plane with conventional three-axis control. Wing has swept back leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin-mounted rudder; roll control by full-span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables and struts; wing profile Clark Y; double-surface. Undercarriage has three wheels in tricycle formation with additional tailskid; rubber suspension on nosewheel and steel-spring suspension on main wheels. Push-right go-right nosewheel steering connected to yaw control. Optional brakes on main wheels. Aluminium-tube framework, partially en-closed. Engine mounted above wing driving tractor propeller.

The PX2000 design studies began in December 1982 following an idea of Patrick Lemonnier. The construction of the prototype was begun in February 1983 and it made its first flight on the 3 April. Its test programme included as much static testing as flight testing, static tests being entrusted to Ingenerie Technique Atlantique (ITA), a specialist aeronautical and marine laboratory.

By 1982 the single-seater had already largely con-firmed the calculated performance figures. The figures quoted below correspond to the prototype which is fitted with a Fuji Robin EC44 2PM, hand-started and developing 43 hp. It was tested without the glass-fibre pod with polycarbonate windscreen, and the three wheel fairings which will be fitted to the production models.

 

Aile-px2000

 

Engine: Robin EC442PM, 53 hp at 6750 rpm    
Prop-eller diameter 65 inch, 1.64m
Toothed-belt reduction, ratio 2.5/1            
Max static thrust 309 lb, 140 kg
Power per unit, area 0.39hp/sq.ft, 4.2 hp/sq.m    
Fuel capacity 1.8 US gal, 6.6 Imp gal, 30.0 litre
Length overall 17.5 ft, 5. 30 m            
Height overall 7.9ft, 2.40m
Wing span 29.9ft, 9.10m                
Chord at root 4.3ft, 1.29 m
Chord at tip 2.7ft, 0.82m                
Dihedral 2 deg
Sweepback 5 deg                    
Tailplane span 8.7 ft, 2.61 m
Fin height 3.9 ft, 1.20 m                
Total wing area 136 sq.ft, 12.6 sq.m
Total aileron area 31.5 sq.ft, 2.92 sq.m        
Fin area 9.1 sq.ft, 0.85 sq.m
Rudder area 7.5 sq.ft, 0.70 sq.m            
Tail-plane area 12.7sq.ft, 1.18 sq.m
Total elevator area 10.3 sq.ft, 0.96 sq.m        
Wing aspect ratio 6.59/1
Wheel track 4.7 ft, 1.40 m                 
Wheelbase 4.7 ft, 1.40 m
Nosewheel diameter overall 10 inch, 25 cm        
Main wheels diameter overall 12 inch, 30cm
Empty weight 3091b, 140kg            
Max take-off weight 574 lb, 260kg
Payload 265 lb, 120kg                
Max wing loading 4.24 lb/sq.ft, 20.7 kg/sq.m
Max power loading 10.83 lb/hp, 4.9kg/hp        
Load factors; +6.0, -4.0 ultimate
Max level speed 87mph, 140kph            
Never exceed speed 106mph, 170kph
Max cruising speed 81mph, 130kph            
Economic cruising speed 65mph, 105kph
Stalling speed 22mph, 35kph            
Max climb rate at sea level 1000ft/min, 5.1m/s
Min sink rate 400fpm at 34 mph, 2.0 m/s at 55 kph    
Best glide ratio with power off 10/1 at 37mph, 60kph
Take-off distance 115 ft, 35 m            
Landing distance 131 ft, 40 m
Service ceiling 10,000 ft, 3050 m            
Range at average cruising speed 218 mile, 350km

 


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