Fouga CM.10
| 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
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
- 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)
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)
- Cruising 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
- Aircraft of comparable role, configuration and era
Notes
References
- 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
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