Dyn'Aero MCR CR100

The CR100 was conceived and optimized for use in flying-clubs The first flight took place in August 1992. The selected motor (180hp and vp prop) is the least expensive, the CR100 can receive various options, including 200hp with a fixed pitch propeller.

A CR100 built from plans will be able to fly under the CNRA (Navigability certificate Restricts Plane). Aircraft from a kit will be able to fly under the CNSK (Special Navigability certificate Kit) / " category; experimental ", according to the country of registration.

CR 100T

The CR100T is a two-seater directly derived from the CR100. The first flights took place in November 2000. With a nose wheel, 180-200 hp, and variable pitch prop, the CR100T was optimized for reliable and intensive school use.

CR 100
Wing span; 8.50 m
Wing area; 10.60 sq.m
Length; 6.8m
Fuel capacity; 85 lt
Empty weight; 550 kg
Empty equipped weight; 850 kg
MTOW; 760 kg
Aileron span; 2.17 m
Aileron surface; 1.21 sq.m
Max manouevre (Va): 260 km/h
Max speed (Vne): 346 km/h
Max turbulent air (Vno); 301 km/h
Design load: +8 /-6 g
Max flap extension (Vfe): 185 km/h
Rate of climb; 8 m/s
Roll rate at 260 km/h; 195 deg/s

CR 100T
Engine: Lycoming O-360, 200 hp
Wing span; 8.50 m
Wing area; 10.60 sq.m
Length; 6.8 m
Fuel capacity; 85 lt
Empty weight; 550 kg
MTOW; 850 kg
Aileron span; 2.17 m
Aileron area; 1.21 sq.m
Manoeuvring speed (Va); 260 km/h
Max speed (Vne); 346 km/h
Max turbulence speed (Vno); 301 km/h
Load factor; +8 /-6 g
Max flap extn (Vfe); 185 km/h
Rate of climb; 8 m/s
Roll rate to 260 km/h; 195 deg/s