Question: 5 . 3 4 Consider an NACA 2 4 1 2 airfoil in a low - speed flow at zero degrees angle of attack and

5.34 Consider an NACA 2412 airfoil in a low-speed flow at zero degrees angle of attack and a Reynolds number of \(8.9\times 10^{6}\). Calculate the percentage of drag from 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 Ch.4.
5 . 3 4 Consider an NACA 2 4 1 2 airfoil in a low

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