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We can get the skin-friction drag coefficient for a laminar flow for a flat plate by using x as chord length in local skin- friction drag coefficient calculation.

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We can get the skin-friction drag coefficient for a laminar flow for a flat plate by using x as chord length in local skin- friction drag coefficient calculation.

(a) True

(b) False

I had been asked this question in examination.

Enquiry is from Laminar Flow in division Incompressible Flow over Airfoils of Aerodynamics

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Correct choice is (b) False

Best explanation: The skin-friction drag coefficient is Cf=\(\frac {1.328}{\sqrt{Re_c}}\) and the local skin-friction drag coefficient is Cf=\(\frac {0.664}{\sqrt{Re_x}}\). Cf is calculated by integrating cf over the whole airfoil chord and as visible by the formula, we cannot get it directly by putting x = c.

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