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Aérokart 4320


A two-seat, side-by-side, single-engined, high-wing monoplanewith conventional three-axis control. The wing has unswept leading edge, swept forward trailing edge and constant chord, cruciform tail. Pitch control is by eleva-tor on tail, and yaw control by fully flying rudder; roll control by half-span ailerons; control inputs through stick for pitch/roll and pedals for yaw. The wing is braced from below by struts; with a double-surface wing profile. The undercarriage has three wheels in tricycle formation; no suspension on the nosewheel and bungee suspen-sion on the main wheels. Push-right go-right nosewheel steering is connected to the yaw control. No brakes. An aluminium-tube framework, without pod, the engine is mounted below wing driving pusher propeller.

On the two-seater Aero-kart 4320 the kingpost and wire used on this company's single-seaters is replaced by struts. The horizontal stabiliser, stiffened in flight and land-ing by cables, has the outer sections of its leading edge joined by tubes to the spars carrying the tail assembly. These tube joints form a structure of high structural integrity rather than low dragThe 4320 has its motor mounted in front of the wing on silent-bloc bushes, driving a twin-bladed propeller behind the trailing edge from toothed-belt reduction. The 1983 standard power pack for this aircraft was the twin-cylinder in-line Hirth 2701R of 43hp fitted with a tuned exhaust for each cylinder, this system having been developed by Aero-kart.The hot air from the cooling fan is fed to the carburettor and air filter by a movable flap when atmospheric conditions demand de-icing and switched back at other times.

This two-seater is delivered in standard form with an electric starter while retaining the capability of manual starting. Electric fuel pump and double surfacing for the wing, ailerons and tail areas, and alloy rims for the main wheels are all standard fittings on the 4320. The machine is transportable on a trailer, folded dimensions being 16.9 x 6.3 x 5.9ft (5.10 x 1.90 x 1.76m).

Engine: Hirth 2701R-03, 43 hp at 6750 rpm
Propeller: 55 x 32 in, 1.40 x 0.80 m        
Reduction ratio: 2.5/1
Power per unit area: 0.19hp/sq.ft, 2.2hp/sq.m        
Max static thrust: 287 lb, 130kg    
Fuel capacity: 5.3 US gal, 4.4 Imp gal, 20.0 lt     
Length overall: 19.0ft, 5.8m
Optional fuel capacity: 7.9 US gal, 6.6 Imp gal, 30.0 lt     
Height overall: 9.8ft, 2.94m
Wing span: 34.5ft, 10.5m             
Chord at root: 6.4 ft, 1.92m
Chord at tip: 6.2ft, 1.89m            
Dihedral: 1.5 deg
Sweepback: 0 deg                
Tailplane span: 9.1 ft, 3.00 m
Total wing area: 216 sq.ft, 20.0 sq.m        
Total aileron area: 12.9 sq.ft, 1.2 sq.m
Rudder area: 12.1 sq.ft, 1.12 sq.m        
Tail-plane area: 21.6 sq.ft, 2.0 sq.m
Total elevator area: 12.3 sq.ft, 1.14 sq.m        
Wing aspect ratio: 5.4/1
Wheel track: 5.7ft, 1.70 m            
Wheelbase: 5.8ft, 1.72m
Nosewheel dia. Overall: 10 in, 26 cm            
Main wheels dia. Overall: 16 in, 40 cm
Empty weight: 322 lb, 146kg            
Max take-off weight: 707 lb, 320kg
Payload: 385 lb, 174 kg            
Load factors: +5.5, -2.5 design
Max wing loading: 3.27 lb/sq.ft, 16.0 kg/m        
Max level speed:     56mph, 90kph
Max power loading: 16.4 lb/hp, 7.44kg/hp        
Never exceed speed: 75mph, 120 kph
Max cruising speed: 50 mph, 80 kph            
Economic cruising speed: 40mph, 65kph
Stalling speed: 22 mph, 35 kph            
Max climb rate at SL: 450 ft/min, 2.3 m/s
Min sink speed: 31 mph, 50 kph             
Min sink rate: 430 ft/min, 2.2 m/s
Best glide ratio: 7/1 at 45 mph, 65 kph
Take-off distance: 230 ft, 70 m
Land-ing distance: 98 ft, 30 m            
Service ceiling: 10,000 ft, 3050 m
Range at ave cruise: 186 mile, 300km.


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