Mean Aerodynamic Chord and Area

[Pulp]

If I have a problem in which the laminar/turbulent transition point is said to be 50% the mean aerodynamic chord, how can I find the area of the wing over which there is laminar flow? Is it simply half the wing area?

 

[bigfooted]

Aerodynamic chord is MAC=S/b, with S the surface area of the wing and b the wing span.
So 50% of MAC, that's 0.5*S/b, so yes, it's half the wing area.