Specifications and Coefficient of Lift for the Dyn-Aero/LAFAYETTE MCR 'Ban-Bi'

[durabol]

I think the CL around 2.5 is with flapperons and the CL around 3.0 is with double slotted fowler flaps.

-MCR VLA Sportster:
Wing span 6.63 m /.0254m / 12=21.7'
Chord=.8m=2.62'
Wing aera 5.20 m² /.0254/.0254/12/12=56sq.ft
Aspect ratio 8.45
Max. Takeoff weight 490 kg / .454 = 1080lbs
VSO (stall speed landing configuration) 87 km/h=54mph*1.47fps/mile=79.4fps
Vne ( Never exceeding speed) 320 km/h=200mph
Vno (Normal Operation Speed) 260 km/h=162mph
G loading +4 /-2 g
Vfe (Flaps extended speed) 170 km/h=106mph
-CL=1080/(.5*.00237*79.4fps^2*56sq.ft)=2.6

-MCR CLUB: direct evolution of the MCR Sportster. It is also a side by side two-seater airplane, it is designed around the same fuselage with an identical cockpit and eng VLAine installation.The MCR Club appears for the first time in 1998
span=6.9m=22.6'
chord=.96m=3.15'
area=6.45m^2 /.0254/.0254/12/12=69.4sq.ft
fuel=80L with optional 2 40L tanks
empty/gross=260kg/490kg=1080lbs
VSO (stall speed landing configuration) 79 km/h=47mph=69.7fps
Vne ( Never exceeding speed) 300 km/h
Vno (Normal Operation Speed) 255 km/h
Vfe (Flaps extended speed) 165 km/h
-CL=1080/(.5*.00237*69.7fps^2*69.4sq.ft)=2.7

-MCR ULC specifications were established in 1996
MCR01 ULC is similar to the 'Club' but with a larger wing span than the 'Club' in order to lower the stall speed for countries such as the UK where the required ultralight stall speed is 35kts
Wing span 8.64 m=28.3'
Wing aera 8.13 m² /.0254/.0254/12/12=87.5sq.ft
Chord .96m=3.15'
Aspect ratio 9.18
Fuel capacity standard 80 l
Extended range fuel tanks 2 x 40 l
Equipped empty weight 270 kg
Max. Takeoff weight 472 kg =1040
VSO (stall speed landing configuration) 63 km/h=55.6fps
Vno (Normal Operation Speed) 210 km/h
G loading +4 /-2 g
Vfe (Flaps extended speed) 140 km/h
-CL=1040/(.5*.00237*55.6fps^2*87.5sq.ft)=3.2

-MCR M is a direct evolution of the MCR ULC. First flight was done in December 1999.
Wing span 8.64 m =28.3'
Wing aera 8.13 m² =87.5sq.ft
Aspect ratio 9.18
Chord .96m=3.15
Fuel capacity standard 80 l
Extended range fuel tanks 2 x 40 l
Empty weight (Basic version 230 kg
Equipped empty weight 270 kg
Max. Takeoff weight 544 kg =1200lbs
VSO (stall speed landing configuration) 70 km/h =61.7fps
Vno (Normal Operation Speed) 221 km/h
G loading +4 /-2 g
Vfe (Flaps extended speed) 140 km/h
-CL=1200/(.5*.00237*61.7fps^2*87.5sq.ft)=3.0

-MCR ULC R is a direct evolution of the MCR ULC. First flight was done in March 2000. The MCR ULC R characteristics lie in its unique wing design, involving a greater span and area, as well as split double slotted fowler flaps and ailerons. This sophisticated wing concept allows the MCR ULC R to reach an unprecedented maximum to stall speed ratio of 4, although it guarantees a very gentle behavior in rough air conditions and a high safety level.
Wing span 8.64 m =28.3'
Wing aera 8.13 m² =87.5sq.ft
Chord .96m=3.15'
Aspect ratio 9.18
Cabin Width 1.12 m
Fuel capacity standard 80 l
Extended range fuel tanks 2 x 40 l
Empty weight (Basic version 230 kg
Equipped empty weight 270 kg
Max. Takeoff weight 490 kg =1080lbs
Wing loading 60 kg/m²
VSO (stall speed landing configuration) 63 km/h 55.6fps
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
-CL=1080/(.5*.00237*55.6fps^2*87.5sq.ft)=3.4

-MCR-4S four-seat 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
Wing span 8.72 m
Wing aera 8.30 m² /.0254/.0254/12/12=89.3sq.ft
Chord=.96m=3.15'
Aspect ratio 9.20
Cabin Width 1.20 m
Fuel capacity standard 2 x 65l
Extended range fuel tanks 2 x 100 l
Empty weight (Basic version 300 kg
Equipped empty weight 350 kg
Max. Takeoff weight 750kg = 1652
Wing loading 90 kg/m²
Rotax 912S Engine 100 hp
Rotax 914 turbo charged Engine 100 hp
Jabiru 3300 Engine 120 hp
VSO (stall speed landing configuration) 83 km/h =49.8mph=73.2fps
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
-CL=1652/(.5*.00237*73.2fps^2*89.3sq.ft)=2.91

Brock

[Typhoon]

Hi !

I don't understand why doesn't match the Wing loading for the MCR Sporter: Wing area= 5,2m² ; MTOW=490Kg -> So...W/S = 94 Kg/m², isn't? Why in the website is 86Kg/m² ? They use flaps fowler (so Area is bigger) to calculate the Wing Loading or what?

source Dynaero website: www.dynaero.com

[clanon]

It's have been achieved historically before on FI-156 fieseler.
(slots+high A/R + fowler flaps)=3.68 CL