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Aeronautic 2000 Baroudeur 2-place


Side-by-side two-seat single-engined high-wing monoplane with conventional three-axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin-mounted rudder; roll control by ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile double-surface. Undercar-riage has three wheels in tricycle formation with additional tailskid; steel-spring suspension on nosewheel and torsion-bar suspension on main wheels. Push-right go-right nose-wheel steering connected to yaw control. Optional brake on nosewheel. Aluminium-tube framework, with optional pod. Engine mounted below wing driving tractor propeller.

Designed by Philippe Tisserand, the two-seat version made its first flight in December 1982. Apart from the engine position, very few changes were deemed necessary on this machine, which is directly descended from the single-seater.

First sales were in February 1983. Like its elder, it is of conventional three-axis control with large control surfaces. The two-seater retains the advantage of being foldable to small dimensions, so it can be car topped or carried on a trailer; folded it measures 16.5 x 1.8 x 1.8ft (5.50 x 0.50 x 0.50m). It is offered as standard with the Hirth 2701R engine of 43hp or the Rotax 503 of 46 hp with toothed-belt reduction. A partial fairing of the cockpit area is offered as an option. Also, Aeronautic 2000 offers it in kit form complete, for export only, a move aimed particularly at the American continent. Composed of pre-formed factory-built units, cut and drilled, this kit requires 100h for assembly. The Baroudeur Biplace is fitted with dual controls as standard version.

Engine: Rotax 503, 46hp at 6500rpm    
Propeller diameter: 63 in, 1.6 m
Reduction ratio: 2.5/1            
Max static thrust: 287 lb, 130 kg
Power per unit area: 0.30hp/sq.ft, 3.3hp/sq.m    
Fuel capacity main: 5.3 US gal, 4.4 Imp gal, 20.0 lt
Fuel capacity reserve: 6.6 US gal, 5.5 Imp gal, 25.0 lt
Length overall: 18.1 ft, 5.5 m        
Height overall: 8.2 ft, 2.5 m
Wing span: 29.6 ft, 9.0 m        
Constant chord: 5.1ft, 1.55m
Dihedral: 2 degs            
Sweepback: 0 degs
Tailplane span: 7.9ft, 2.40 m        
Total wing area: 151 sq.ft, 14.0 sq.m
Total aileron area: 16.2 sq.ft, 1.5 sq.m    
Rudder area: 7.5 sq.ft, 0.7 sq.m
Fin area: 4.3 sq.ft, 0.4 sq.m        
Tailplane area: 16.2 sq.ft, 1.5 sq.m
Total elevator area: 9.7 sq.ft, 0.9 sq.m        
Wing aspect ratio: 5.78/1
Wheel track: 4.5 ft, 1.35 m         
Wheelbase: 4.9 ft, 1. 45 m
Nosewheel dia. Overall: 12 in, 30 cm        
Main wheels dia. Overall: 12 in, 30cm
Empty weight: 287 lb, 130kg        
Max take-off weight: 662 lb, 300kg
Payload: 375 lb, 170kg        
Max wing loading: 4.38 lb/sq.ft, 21.4kgsq.m
Max power loading: 14.4 lb/hp, 6.5kg/hp    
Load factors: +6, -2.5 design
Max level speed: 62 mph, 100 kph        
Never exceed speed: 71 mph, 115 kph
Max cruising speed: 56 mph, 90 kph        
Economic cruise: 50 mph, 80 kph
Stalling speed: 24 mph, 40 kph        
Max climb rate SL: 600ft/min, 3.0m/s
Min sink speed: 37 mph, 60 kph        
Min sink rate: 350 ft/min, 1.7 m/s
Best glide ratio: 10/1 at 37 mph, 60 kph    
Take-off distance: 165 ft, 50 m.
Land-ing distance: 165 ft, 50 m        
Service ceiling: 10,000ft, 3050 m
Range at ave. cruise: 186 mile, 300 km
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