DYNAERO MCR 4 S

The initial studies of the four-seat MCR-4S started in early 1994 while we were developing the MCR VLA. The VLA appears first in 1996 and permits 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 command system was directly coming from the MCR CLUB technology in 1998.
The objective was to develop, what most thought impossible at that time:

“ A four seat airplane with STOL performance, equipped with a light 100 HP engine” 

The 4-S maiden flight was in June 2000. 

The MCR 4-S is the only airplane in the aviation world to provide pilots with such an amazing Performance/Economy ratio. Its concept makes it to be the perfect travel aircraft, able to fly comfortably with four people onboard, cruising at more than 250 km/h, and burning only 20 L/h with a 100 hp engine.
Those performances can only be reached because of the MCR 4-S very light empty weight . The aircraft can carry up to 150% of its own empty weight !
The research of a very elaborated aerodynamic design, with wing-tips optimized in wind-tunnel, and high efficiency double slotted flaps, provide the MCR 4-S with amazing STOL performances
Designed around a roomy cockpit ; 1,20m width at the rear seats, build 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 MCR-4S  can be  equipped with a choice of different power plants, but may also be fitted with other options such as : 

Ballistic Recovery System parachute(actually in development)

Extended range fuel tanks

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.

 GENERAL CARACTERISTICS

Wing span....................................................................... 8,72 m

Wing area ..................................................................... 8,30 m²

Aspect ratio.......................................................................... 9,20

Cabin Width ....................................................................... 1,20

Fuel capacity standard................................................ 2 X 65 l

Extended range fuel tanks....................................... 2 X 100 l

Empty weight (Basic version) ..................................... 300 kg

Equipped empty weight................................................ 350 kg

Max. Takeoff weight ...................................................... 750 kg

Wing loading............................................................... 90 kg/m²

 

ENGINE OPTIONS

Propeller :Two, or three blades, fix pitch or constant speed

Rotax 912S Engine....................................................... 100 hp

Rotax 914 turbo charged Engine....................... 100/115 hp

Jabiru 3300 Engine (still in development)............... 120 hp

 

V Speed

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

PERFORMANCES