Fouga CM.10

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CM.10
Role Airliner
Manufacturer Fouga
Designer Robert Castello
First flight 7 June 1947[1]
Number built 7[1]

The Fouga CM.10 was an assault glider designed for the French Army shortly after World War II, capable of carrying 35 troops, later converted as a powered transport.[1]

Design & Development[edit]

The CM.10 was a high-wing cantilever monoplane of conventional configuration with fixed tricycle undercarriage. Flight trials with the glider prototypes were of mixed results with the first prototype crashing on 5 May 1948 whilst being flown by CEV Brétigny. A production order for 100 was placed with Fouga, but cancelled after only 5 gliders had been built.[1]

Undaunted, Fouga adapted the design as an airliner, adding two SNECMA 12S piston engines. Two of the production CM.10 gliders were converted to the powered version, CM.100-01, the first prototype (registration F-WFAV), was first flown on 19 January 1949, but no order resulted for this aircraft. It was later tested with Turbomeca Piméné turbojets mounted on the wingtips as the CM.101R-01. The second aircraft, which was converted as CM.101R-02, (registration F-WFAV), was first flown on 23 Aug 1951.[1]

Variants[edit]

CM.10
The original assault glider design, two prototypes built; CM.10-01, first flight 7 June 1947 at Mont de Marsan, crashed on 5 may 1948 whilst on trials at CEV Brétigny; CM.10-02 was first flown in late 1948. Production orders for 100 were cancelled after five gliders were built.[1]
CM.100
Two CM.10 production gliders powered by two SNECMA 12S-02 engines in nacelles on each wing.[1]
CM.101R
The two CM.100s fitted with auxiliary Turbomeca Piméné turbojets on the wing-tips.[1]
CM.103R

A proposed military transport derivative with Turbomeca Marboré wing-tip auxiliary turbojets.[1]


Specifications (CM.100)[edit]

Data from [1]

General characteristics

  • Crew: two pilots
  • Capacity: 15 passengers / 2,033 kg (4,482 lb) freight
CM.10 - 35 troops (1 x crew) / 3,500 kg (7,716 lb) freight
  • Length: 17.9 m (58 ft 9 in)
  • Wingspan: 26.7 m (87 ft 7 in)
  • Wing area: 71.9 m2 (774 sq ft)
  • Empty weight: 2,833 kg (6,246 lb)
  • Gross weight: 6,420 kg (14,154 lb)
  • Cargo hold capacity: 32 m3 (1,130 cu ft)
  • Powerplant: 2 × SNECMA 12S-02 inverted V-12 air-cooled piston engines, 433 kW (581 hp) each
  • Propellers: 3-bladed variable-pitch propellers

Performance

  • Maximum speed: 280 km/h (174 mph; 151 kn)
  • Cruise speed: 246 km/h (153 mph; 133 kn) at 1,500 m (4,921 ft)
  • Range: 1,000 km (621 mi; 540 nmi) with 14 passengers and 182 kg (401 lb) baggage

See also[edit]

Aircraft of comparable role, configuration and era

Notes[edit]

  1. ^ a b c d e f g h i j Chillon, J.; J-P Dubois; J. Wegg (1980). French Postwar Transport Aircraft (1st ed.). Tonbridge: Air-Britain (Historians) Ltd. pp. 145 &153–154. ISBN 0-85130-078-2. 

References[edit]

  • Chillon, J.; J-P Dubois; J. Wegg (1980). French Postwar Transport Aircraft (1st ed.). Tonbridge: Air-Britain (Historians) Ltd. pp. 145 &153–154. ISBN 0-85130-078-2. 

External links[edit]