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Dyn’Aero MCR ULC / Minicruiser

 

mcrulc


The MCR ULC specifications were established in 1996, defining it as an ultra-light airplane based on the FAI requirements, and first flown in April 1997. Based on the Sportster design, with the same fuselage and engine installation, the FAI ultralight MCR-ULC was specifically designed for fast cruise and optimized for slow approach speeds.


The MCR ULC characteristics lie in its wing design, involving a greater span and area, as well as split double slotted fowler flaps and ailerons.


The MCR ULC can be equipped with a choice of different power plants, but may also be fitted with other options such as Ballistic Recovery System parachute, Oil Pneumatic under carriage ( for intensive use), extended ferrying fuel, toe operated Hydraulic brakes, and fuselage footsteps. Engine options include the 80 hp Rotax 912, 100 hp Rotax 912S, and 80 hp Jabiru 2200.


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


Ready-to-fly delivered aircraft are in the Ultra-light category

The MCR ULC R is a direct evolution of the MCR ULC, available in kit form in respect with the CNSK regulation (specific kit airworthiness certificate) or in the "experimental" category, depending on the registration country.


Engine options include the 80 hp Rotax 912, 100 hp Rotax 912S, 100 hp turbo charged Rotax 914, and 80 hp Jabiru 2200.



mcrulcdrw
MCR ULC R


The MCR M is a tail wheel evolution of the MCR ULC R, first flown in December 1999.


The MCR M 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.

mcrm
MCR M




mcrmdrw
MCR M



dynaerominicruiser
MCR MiniCruiser


Turbo, rescue parachute, autopilot. Price 2009: 100000 EURO

MCR ULC
Wing span; 8.64 m
Wing aera; 8.13 sq.m
Aspect ratio; 9.18
Cabin Width; 1.12 m
Fuel capacity standard; 80 lt
Extended range fuel tanks; 2 x 40 lt
Empty weight Basic version; 230 kg
Equipped empty weight; 270 kg
Max. Takeoff weight; 472 kg
Wing loading; 58 kg/sq.m
VSO (stall speed landing configuration); 63 km/h
Va (Maneuvering speed); 172 km/h
Vne ( Never exceeding speed); 270 km/h
Design maneuvering speed; 300 km/h
Vno (Normal Operation Speed); 210 km/h
G loading; +4 /-2 g
Vfe (Flaps extended speed); 140 km/h

Engine; Rotax 912, 80 hp
Cruising 75%, FL 0; 250 km/h
Cruising 75%, FL 80; 270 km/h
Fuel consumption 75%; 17,1 lt/hr
Range ,std Tanks 75%; 1245 km
Cruising 65% FL110; 265 km/h
Fuel consumption 65%; 14,8 lt/hr
Range ,std Tanks 65%; 1432 km
Takeoff roll; CS. Prop; 140 m
Climb rate FL 0, CS; 1750 fpm

Engine; Rotax 912S, 100 hp
Cruising 75%, FL 0; 271 km/h
Cruising 75%, FL 80; 293 km/h
Fuel consumption 75%; 21,3 lt/hr
Range ,std Tanks 75%; 1097 km
Cruising 65% FL110; 288 km/h
Fuel consumption 65%; 18,5 lt/hr
Range ,std Tanks 65%; 1264 km
Takeoff roll; CS. Prop; 112 m
Climb rate FL 0, CS. Prop; 1950 fpm

MCR ULC R

Wing span; 8.64 m
Wing aera; 8.13 sq.m
Aspect ratio; 9.18
Cabin Width; 1.12 m
Fuel capacity standard; 80 l
Extended range fuel tanks; 2 x 40 lt
Empty weight Basic version; 230 kg
Equipped empty weight; 270 kg
Max. Takeoff weight; 490 kg
Wing loading; 60 kg/sq.m
VSO (stall speed landing configuration); 63 km/h
Va (Maneuvering speed); 172 km/h
Vne ( Never exceeding speed); 270 km/h
Design maneuvering speed; 300 km/h
Vno (Normal Operation Speed); 210 km/h
G loading; +4 /-2 g
Vfe (Flaps extended speed); 140 km/h

Engine; Rotax 912, 80 hp
Cruising 75%, FL 0; 250 km/h
Cruising 75%, FL 80; 270 km/h
Fuel consumption 75%; 17,1 lt/hr
Range ,std Tanks 75%; 1245 km
Cruising 65% FL110; 265 km/h
Fuel consumption 65%; 14,8 lt/hr
Range ,std Tanks 65%; 1432 km
Takeoff roll; CS. Prop; 140 m
Climb rate FL 0, CS. Prop; 1750 fpm

Engine; Rotax 912S, 100 hp
Cruising 75%, FL 0; 271 km/h
Cruising 75%, FL 80; 293 km/h
Fuel consumption 75%; 21,3 lt/hr
Range ,std Tanks 75%; 1097 km
Cruising 65% FL110; 288 km/h
Fuel consumption 65%; 18,5 lt/hr
Range ,std Tanks 65%; 1264 km
Takeoff roll; CS. Prop; 112 m
Climb rate FL 0, CS. Prop; 1950 fpm

MCR M
Wing span; 8.64 m
Wing aera; 8.13 sq.m
Aspect ratio; 9.18
Cabin Width; 1.12 m
Fuel capacity standard; 80 lt
Extended range fuel tanks; 2 x 40 lt
Empty weight Basic version; 230 kg
Equipped empty weight; 270 kg
Max. Takeoff weight; 544 kg
Wing loading; 67 kg/sq.m
VSO (stall speed landing configuration); 70 km/h
Va (Maneuvering speed); 191 km/h
Vne ( Never exceeding speed); 315 km/h
Design maneuvering speed; 350 km/h
Vno (Normal Operation Speed); 221 km/h
G loading; +4 /-2 g
Vfe (Flaps extended speed); 140 km/h

Engine; Rotax 912, 80 hp
Cruising 75%, FL 0; 250 km/h
Cruising 75%, FL 80; 270 km/h
Fuel consumption 75%; 17,1 lt/hr
Range ,std Tanks 75%; 1245 km
Cruising 65% FL110; 265 km/h
Fuel consumption 65%; 14,8 lt/hr
Range ,std Tanks 65%; 1432 km
Takeoff roll; CS. Prop; 140 m
Climb rate FL 0, CS. Prop; 1750 fpm

Engine; Rotax 912S, 100 hp
Cruising 75%, FL 0; 271 km/h
Cruising 75%, FL 80; 293 km/h
Fuel consumption 75%; 21,3 lt/hr
Range ,std Tanks 75%; 1097 km
Cruising 65% FL110; 288 km/h
Fuel consumption 65%; 18,5 lt/hr
Range ,std Tanks 65%; 1264 km
Takeoff roll; CS. Prop; 112 m
Climb rate FL 0, CS. Prop; 1950 fpm

DynAero MCR MiniCruiser
Stall: 49 kt / 56 mph / 91 kmh
Cruise: 172 kt / 198 mph / 319 kmh
VNE: 175 kt / 201 mph / 324 kmh
Empty Weight: 250 kg / 551 lbs
MTOW Weight: 490 kg / 1080 lbs
Climb Ratio: 1750 ft/min / 9 m/s
Glide Ratio: 10
Take-off distance (50ft obstacle): 200 ft / 61 m
Landing distance (50ft obstacle): 350 ft / 107 m

 


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