SECAN Courlis

SUC-10 Courlis
	SECAN SUC-10 Courlis at Sherburn-in-Elmet, Yorkshire, July 1951
Role	Touring cabin monoplane
National origin	France
Manufacturer	SECAN
First flight	9 May 1946
Number built	144

The SECAN SUC-10 Courlis (en: Curlew) was a French high-wing touring monoplane designed and built by Société d'Etudes et de Construction Aéronavales (SECAN), a branch of the automobile company Société des Usines Chaussons. The aircraft had problems with the engine installation and only 144 were built, some without engines and were scrapped.

Development

The Courlis was an all-metal high-wing cantilever monoplane with twin booms supporting a tail unit. It was powered by a 190 hp (142 kW) Mathis G8R piston engine mounted in the rear fuselage in a pusher configuration. It had a fixed tricycle landing gear and had four seats in the enclosed cabin. The prototype, registered F-WBBF, first flew on 9 May 1946.^[1] Production was started and a total of 144 aircraft were completed with a number being exported to South America. Problems with the engine (insufficient power, cooling)^[2] resulted in the withdrawal of the engine's type certificate and some airframes were never fitted with an engine and scrapped. The company did test fit the aircraft with a 220 hp (164 kW) Mathis engine but production was ended.

The aircraft flew for some years, owned by French private pilots, but by the mid-1950s, most had been withdrawn from service, with many being stored at Mitry-Mory airfield near Paris.

In 1961 the design was revised as the SUC-11G Super Courlis with a 240 hp (179 kW) Continental O-470M engine, but was abandoned after a prototype was built.

Variants

SUC-10 Courlis: Production variant with a 190hp Mathis G.8R engine, 144 built (not all flown).
SUC-11G Super Courlis: Improved design with a 240hp Continental O-470M engine, only one built.

Aircraft on display

One aircraft is held by the Musée de l'Air et de l'Espace, Le Bourget, Paris, France, but is not currently (2007) on public display.

Specifications (SUC-10 Courlis)

Data from ,^[3] Jane's all the World's Aircraft 1947^[4]

General characteristics

Crew: 1 (pilot)
Capacity: 3 passengers
Length: 8.18 m (26 ft 10 in)
Wingspan: 12.35 m (40 ft 6 in)
Height: 2.68 m (8 ft 10 in)
Wing area: 19.10 m² (205.6 sq ft)
Empty weight: 895 kg (1,973 lb)
Gross weight: 1,439 kg (3,172 lb)
Max takeoff weight: 1,560 kg (3,439 lb)
Fuel capacity: 200 L (53 US gal; 44 imp gal) in two centre-section tanks
Powerplant: 1 × Mathis G.8R-40 air-cooled inverted-V piston engine, 149 kW (200 hp)
Propellers: 2-bladed wooden fixed-pitch pusher propeller

Performance

Maximum speed: 250 km/h (160 mph, 130 kn)
Cruise speed: 220 km/h (140 mph, 120 kn) (70% power)
Landing speed: 80 km/h (50 mph; 43 kn)
Range: 1,230 km (760 mi, 660 nmi) with pilot and three passengers + luggage
Service ceiling: 5,000 m (16,000 ft)

References

Notes

^ Simpson 1991, page 362
^ Pegase n°58, La formule des appareils bipoutres à moteur propulsif, Jacques Noetinger
^ Donald 1997, p. 796
^ Bridgman, Leonard, ed. (1947). Jane's all the World's Aircraft 1947. London: Sampson Low, Marston & Co. pp. 131c–132c.

Bibliography

Donald, David, ed. The Complete Encyclopedia of World Aircraft. London: Orbis, 1997. p. 796. ISBN 0-7607-0592-5.
Simpson, R.W. (1991). Airlife's General Aviation. England: Airlife Publishing. ISBN 1-85310-194-X.
Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions.
The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing.

[1] Simpson 1991, page 362

[2] Pegase n°58, La formule des appareils bipoutres à moteur propulsif, Jacques Noetinger

[3] Donald 1997, p. 796

[JAWA1947-4] Bridgman, Leonard, ed. (1947). Jane's all the World's Aircraft 1947. London: Sampson Low, Marston & Co. pp. 131c–132c.

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