avia.wikisort.org - Glider
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]
| CM.10 | |
|---|---|
 | |
| Role | Airliner |
| Manufacturer | Fouga |
| Designer | Robert Castello |
| First flight | 7 June 1947[1] |
| Number built | 7[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 (170 mph, 150 kn)
- Cruise speed: 246 km/h (153 mph, 133 kn) at 1,500 m (4,921 ft)
- Range: 1,000 km (620 mi, 540 nmi) with 14 passengers and 182 kg (401 lb) baggage
See also
Aircraft of comparable role, configuration, and era
Notes
- 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
- 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
На других языках
- [en] Fouga CM.10
[fr] Fouga CM.10
Le Fouga CM.10 était un prototype de planeur militaire, conçu en France par les ingénieurs Robert Castello et Pierre Mauboussin chez Fouga.Другой контент может иметь иную лицензию. Перед использованием материалов сайта WikiSort.org внимательно изучите правила лицензирования конкретных элементов наполнения сайта.
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