Mudry CAP 10

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The Mudry CAP 10 is a two-seat training aerobatic aircraft first built in 1970 and still in production in 2007. The plane was developed from the Piel Super Emeraude and was born as the CP100. The name changed to CAP 10, CAP for 'Constructions Aéronautiques Parisiennes'. The CAP 10 was manufactured by Mudry (name of its designer) in Bernay, France, bought by CAP Industries which then became Apex Aircraft. Following the bankruptcy of Apex in 2008, rights to produce spares were awarded to Dyn'Aviation.^[1]

Design and development

The prototype CAP 10 was first flown in August 1968 it was followed by the production variant the CAP 10B which had revised tail surfaces. The CAP 10 is a low-wing cantilever monoplane of wooden construction on the 'B' version and carbon sandwich wing spar on the recent Cap 10C version. The engine is a 180 hp Lycoming AEIO-360 fuel injection engine, fully lubricated in inverted flight.

300+ aircraft were built, and, in 2007, the CAP 10C is still in production.

The CAP 10 is one of the most successful aerobatic training aircraft in the world, around 200 aircraft are still flying in the late 2000s and nearly two generations of aerobatic champions made their classes with it.

In the late 70's the CAP 10 was developed to the single seater family of the CAP 20, 20L and 21. In the 1980s, a far derivative was the most successful family of the Cap 23x competition single seaters.

Operators

Military

France

French Air Force ^[2]
French Navy ^[2]

Morocco: Used to train pilots
Mexico: The Mexican Air Force bought 20^[2]
South Korea
Australia: Formerly used by the Royal Australian Air Force, Royal Australian Navy and the Australian Army to select new pilots.

Civilian

More than 200 were built, mostly for airclubs all around the world. A huge number of European champions have started aerobatics on a Cap 10.

Specifications (CAP 10B)

Data from Jane's All The World's Aircraft 1988-89 ^[3]

General characteristics

Crew: 2
Length: 7.16 m (23 ft 6 in)
Wingspan: 8.06 m (26 ft 5¼ in)
Height: 2.55 m (8 ft 4½ in)
Wing area: 10.85 m² (116.8 sq ft)
Airfoil: NACA 23012
Empty weight: 540 kg (1,190 lb)
Max. takeoff weight: 830 kg (1,829 lb)
Powerplant: 1 × Lycoming AEIO-360-B2F 4-cylinder air-cooled, horizontally opposed, fuel injected piston engine, 180 hp (134 kW)

Performance

Never exceed speed: 340 km/h (183 knots, 211 mph)
Maximum speed: 270 km/h (146 knots, 168 mph) at sea level
Cruise speed: 250 km/h (135 knots, 155 mph) (75% power)
Stall speed: 85 km/h (46 knots, 53 mph) (full flaps)
Range: 1,200 km (647 nmi, 745 mi)
Service ceiling: 5000 m (16,400 ft)
Rate of climb: Over 6 m/s (1,180 ft/min)
G-loads: version +6; -4,5g

References

Wikimedia Commons has media related to CAP-10.

↑ "News" Aerodif. Retrieved 10 October 2009.
↑ 2.0 2.1 2.2 Taylor 1988, p.78.
↑ Taylor 1988, pp. 78—79.

Taylor, John W.R. Jane's All The World's Aircraft 1988-89. Coulsdon, UK:Jane's Defence Data, 1988. ISBN 0-7106-0867-5

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