Aviasud Mistral

Mistral
Role	Ultralight biplane
National origin	France
Manufacturer	Aviasud Engineering
First flight	1985
Introduction	1986
Number built	250+ (1999)

The Aviasud Mistral is a French two-seat ultralight biplane built by Aviasud Engineering. This plane is notable as it has forward swept wings and side-by-side seating. The lower wings are movable and are used as the roll control (wing leveler).

The aeroplane (along with the Sirocco) was taken over, and is still supported by, Aériane in 1989.^[1]

Design and development

The Aviasud Mistral has a biplane configuration

The Aviasud Mistral was designed by two Belgian engineers, Francois Goethals and Bernard d'Otreppe.

The prototype first flew in May 1985,^[2] and the aircraft entered production with AviaSud engineering in Fréjus,^[3] with the first production model having its maiden flight in February 1986.^[2] Aviasud has built more than 200 Mistrals, it has also been built by Ultraleger Industria Aeronáutica Ltda in Brasil.^[1]

The Mistral is a biplane of mixed wooden and composite construction, with forward swept wings, with the all-moving lower wings used as large ailerons, and a conventional, all-moving tailplane. It has a fixed tricycle landing gear and a nose-mounted Rotax piston engine. The Mistral has an enclosed cockpit with two side-by-side seats forward of the wings.^[1]^[2]

On May 4, 1987, an Aviasud Mistral was flown to the geographic North Pole by Nicolas Hulot, a world first for this type of aircraft.

Variants

Mistral: Original version with 47 kW Rotax 532 engine.^[5]
Mistral 503: Low powered, economy version with 37 kW (50 hp) Rotax 503 engine.^[6]
AE 206 Mistral: Basic version, powered by 48 kW (64 hp) Rotax 582 engine.^[2]
AE 206 US: "Ultra Silent" version with larger, lower geared propeller.^[2]
AE 207 Mistral Twin: Twin engined version for advertising and surveillance work, with additional, pusher Rotax 503 engine above wing.^[2] 30 built by 1999.^[1]

Specifications (AE 206)

Data from Jane's All The World's Aircraft 1993-94 ^[2]

General characteristics

Crew: 1
Capacity: 1 passenger
Length: 5.66 m (18 ft 7 in)
Wingspan: 9.40 m (30 ft 10 in)
Height: 2.25 m (7 ft 5 in)
Wing area: 16.39 m² (176.4 sq ft)
Airfoil: NACA 23012
Empty weight: 205 kg (452 lb)
Max takeoff weight: 390 kg (860 lb)
Fuel capacity: 60 L (16 US gal; 13 imp gal)
Powerplant: 1 × Rotax 582 two-stroke, two-cylinder water-cooled piston engine, 48 kW (64 hp)

Performance

Maximum speed: 155 km/h (96 mph, 84 kn)
Cruise speed: 90 km/h (56 mph, 49 kn) (econ. cruise)
Never exceed speed: 165 km/h (103 mph, 89 kn)
Range: 530 km (330 mi, 290 nmi)
Service ceiling: 4,575 m (15,010 ft) (at least)
Rate of climb: 3.9 m/s (760 ft/min)
Takeoff distance to 15 m (50 ft): 200 m (656 ft)
Landing distance from 15 m (50 ft): 225 m (738 ft)

References

Notes

^ ^a ^b ^c ^d Taylor 1999, p.414.
^ ^a ^b ^c ^d ^e ^f ^g Lambert 1993, p.75.
^ Lambert 1993, p.74.
^ "François Goethals and Bernard D'Otreppe". Retrieved 30 October 2017.
^ Taylor 1988, p.519.
^ Taylor 1988, p.520.

Bibliography

Lambert, Mark (ed.). Jane's All The World's Aircraft 1993-94. Coulsdon, UK: Jane's Data Division, 1993. ISBN 0-7106-1066-1.
Taylor, John W.R. Jane's All The World's Aircraft 1988-89. Jane's Defence Data, 1988. ISBN 0-7106-0867-5.
Taylor, Michael J.H. (ed.). Brassey's World Aircraft & Systems Directory 1999/2000. London:Brassey's, 1999. ISBN 1-85753-245-7.
[1] (in Dutch)

[Brasseys_99_p414-1] Taylor 1999, p.414.

[Janes_93_p75-2] ^ ^a ^b ^c ^d ^e ^f ^g Lambert 1993, p.75.

[Janes_93_p74-3] Lambert 1993, p.74.

[vieuxdebs-4] "François Goethals and Bernard D'Otreppe". Retrieved 30 October 2017.

[Janes_88_p519-5] Taylor 1988, p.519.

[Janes_88_p520-6] Taylor 1988, p.520.

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