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Dyn'Aero MCR4S / Pick-up

 

dynaeromcr4s


The initial studies of the four-seat MCR-4S started in early 1994, during development of the MCR VLA. The VLA appears first in 1996 and permited the development of the general technology. The airframe, and the high lift devices, such as the double slotted flaps were initially designed to equipped the MCR UL, meanwhile, the control system was directly from the MCR CLUB technology of 1998.


The MCR 4-S concept was to fly with four people onboard, cruising at more than 250 km/h, and burning only 20 lt/hr with a 100 hp engine.


The research gave wing-tips optimized in a wind-tunnel, and double slotted flaps, providing the MCR 4-S with STOL performances.


Designed around a roomy cockpit ; 1,20m width at the rear seats, to allow four people up to 1,95m tall to be easily seated in the airplane, the aircraft is equipped with a very strong oil-pneumatic undercarriage, allowing landings on any type of runways.


The 4-S maiden flight was in June 2000.


The MCR 4-S has a very light empty weight . The aircraft can carry up to 150% of its own empty weight.


Engine options include the 100 hp Rotax 912S, 100 hp turbo charged Rotax 914, and 120 hp Jabiru 3300.


The MCR-4S can be fitted with other options such as Ballistic Recovery System parachute, extended range fuel tanks, and toe operated hydraulic brakes.


The MCR-4S is available in kit form in respect with the CNSK regulation (specific kit airworthiness certificate) or in the "experimental" category ,depending on the registration country.

 

Dyn-4S-2

 

The MCR PickUp is a two seater version of the MCR 4S with a large trunk instead of the rear seats.

 

Wing span; 8.72 m
Wing aera; 8.30 sq.m
Aspect ratio; 9.20
Cabin Width; 1.20 m
Fuel capacity standard; 2 x 65 lt
Extended range fuel tanks; 2 x 100 lt
Empty weight Basic version; 300 kg
Equipped empty weight; 350 kg
Max. Takeoff weight; 750kg
Wing loading; 90 kg/sq.m
VSO (stall speed landing configuration); 83 km/h
Va (Maneuvering speed); 219 km/h
Vne ( Never exceeding speed); 270 km/h
Design maneuvering speed; 300 km/h
Vno (Normal Operation Speed); 243 km/h
G loading; +3.8 /-1.5 g
Vfe (Flaps extended speed); 160 km/h

Engine; Rotax 912, 95-100 hp
Cruising 75%, FL 0; 245 km/h
Cruising 75%, FL 80; 236 km/h
Fuel consumption 75%; 20.7 lt/hr
Range ,std Tanks 75%; 1079 km
Cruising 65% FL110; 255 km/h
Fuel consumption 65%; 17.9 lt/hr
Range ,std Tanks 65%; 1846 km
Takeoff roll; CS. Prop; 350 m
Climb rate FL 0, CS. Prop; 750 fpm

Engine; Rotax 914, 100-115 hp
Cruising 75%, FL 0; 245 km/h
Cruising 75%, FL 80; 272 km/h
Fuel consumption 75%; 20.7 lt/hr
Range ,std Tanks 75%; 1079 km
Cruising 65% FL110; 255 km/h
Fuel consumption 65%; 17.9 lt/hr
Range ,std Tanks 65%; 1846 km
Takeoff roll; CS. Prop; 350 m
Climb rate FL 0, CS. Prop; 900 fpm

DynAero MCR Pick-up
Stall: 34 kt / 39 mph / 63 kmh
Cruise: 135 kt / 155 mph / 250 kmh
VNE: 146 kt / 168 mph / 270 kmh
Empty Weight: 260 kg / 573 lbs
MTOW Weight: 600 kg / 1323 lbs
Climb Ratio: 1250 ft/min / 6 m/s
Take-off distance (50ft obstacle): 240 ft / 73 m
Landing distance (50ft obstacle): 350 ft / 107 m

 

mcr4sdrw



 


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