Fouga CM.10

__NOTOC__ Infobox Aircraft
name=CM.10


caption=
type=Airliner
manufacturer=Fouga
designer=
first flight=7 June 1947
introduced=
retired=
status=
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produced=
number built=3
variants with their own articles=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.

pecifications (CM.100)

aerospecs
met or eng?= met

crew=two pilots
capacity=14 passengers
length m=17.90
length ft=58
length in=9
span m=26.70
span ft=87
span in=7
dia m=
dia ft=
dia in=
height m=
height ft=
height in=
wing area sqm=71.9
wing area sqft=774
rot area sqm=
rot area sqft=
aspect ratio=
empty weight kg=4,540
empty weight lb=10,010
gross weight kg=7,300
gross weight lb=16,100

eng1 number=2
eng1 type=SNECMA 12S-02
eng1 kw= 433
eng1 hp= 580
eng1 kn=
eng1 lbf=
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eng1 lbf-ab=
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max speed kmh=
max speed mph=
max speed mach=
cruise speed kmh= 245
cruise speed mph= 153
range km=500
range miles=312
endurance h=
endurance min=
ceiling m=
ceiling ft=
glide ratio=
climb rate ms=
climb rate ftmin=
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armament1=
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References

*
* [http://www.aviafrance.com/2148.htm aviafrance.com]

ee also

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