Wind tunnel tests yield the following data for lift coefficient and pitch moment coefficient about the half-chord line of a given wing: (deg) -4.0 -2.0 0.0 2.0 4.0 6.0 8.0 10.0 CL Cmy/2 -0.195 0.123 0.056 0.091 0.194 0.055 0.375 0.621 0.007 -0.032 0.874 -0.048 1.024 -0.096 1.243 -0.141 1. Using the software package of your choice (e.g.. Matlab or Excel), determine C(a) and Cm/2 () using a linear least squares fit. Plot the data and the linear curve fits. 2. Determine hac and Cmac 3. Determine hep for the following three values of lift coefficient: CLE {0.2, 0.4, 0.6}.