For the Laminar Flow NACA 64-210 airfoil in Problem 5.43, what percentage of the total drag is due to skin friction? Assume that the skin friction drag on the airfoil is essentially that for a flat plate, and that the boundary layer is laminar and incompressible.
Problem 5.43
The wing model in Problem 5.42 is replaced with a model with an NACA 64-210 Laminar Flow Airfoil at the same conditions as in Problem 5.42.
a. What is the angle of attack of the model?
b. What is the total drag force on the model?
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