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Mean Aerodynamic Chord and Area

  1. Feb 22, 2014 #1
    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?
  2. jcsd
  3. Feb 23, 2014 #2
    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.
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