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Fouga CM.10 Aircraft Information

Fouga CM.10


Manufacturer: Fouga
First flight: 7 June 1947
Number built: 3

The Fouga CM.10 was an assault glider designed for the French Army shortly after World War II, capable of carrying 35 troops. It was a high-wing cantilever monoplane of conventional configuration with fixed tricycle undercarriage. Two examples were built for evaluation, but no purchase order ensued.

Undaunted, Fouga adapted the design as an airliner, adding two SNECMA 12S piston engines. A single prototype of this powered version, designated CM.100 (registration F-WFAV) the prototype was first flown on 19 January 1949, but no order resulted for this aircraft either. It was later tested with Turboméca Piméné turbojets mounted on the wingtips as the CM.101R.

Specifications (CM.100)

General characteristics

Crew: two pilots
Capacity: 14 passengers
Length: 17.90 m (58 ft 9 in)
Wingspan: 26.70 m (87 ft 7 in)
Wing area: 71.9 m² (774 ft²)
Empty weight: 4,540 kg (10,010 lb)
Gross weight: 7,300 kg (16,100 lb)
Powerplant: 2 x— SNECMA 12S-02, 433 kW (580 hp) each


Cruising speed: 245 km/h (153 mph)
Range: 500 km (312 miles)

Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. pp. 239.

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Source: WikiPedia

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