A wing whose chord dimension is 0.5 m and whose span b is 4m is mounted in a wind tunnel. The profile of the wing is a NACA 23008 airfoil. The free-stream velocity is 60m/s. The density of air is 1.225kg/m^3, and the absolute viscosity is 1.7894x105 kg/m/s. Assume that the flow is two-dimensional and that the critical Reynolds number for this kind of flow is 600,000. a/ Estimate the skin friction drag coefficient for the airfoil. Explain and justify how you obtained the answer and why you are using these equations. b/ Estimate the drag (in Newtons) due to friction for the entire wing using the result found in a/