Consider an NACA 2412 airfoil in a low speed flow at zero degrees angle of attack and a Reynolds number of 8.9 × 106. Calculate the percentage of drag that is due to pressure drag due to flow separation (form drag). Assume a fully turbulent boundary layer over the airfoil. Assume that the airfoil is thin enough that the skin-friction drag can be estimated by the flat plate results discussed in Chapter 4.
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