Problem 2. Wind tunnel tests yield the following data for lift coefficient and pitch moment coefficient about the half-chord line of a given wing: a (deg)CL Cm -4.0 2.0 0.0 0.1950.123 0.056 0.091 0.1940.055 0.375 0.007 0.621-0.032 0.874 |-0.048 1.024 -0.096 1.2430.141 4.0 6.0 8.0 10.0 1. Using the software package of your choice (e.g., Matlab or Excel), determine CL(i) and Crn1/2 () 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: CL E 10.2,0.4,0.6) Problem 2. Wind tunnel tests yield the following data for lift coefficient and pitch moment coefficient about the half-chord line of a given wing: a (deg)CL Cm -4.0 2.0 0.0 0.1950.123 0.056 0.091 0.1940.055 0.375 0.007 0.621-0.032 0.874 |-0.048 1.024 -0.096 1.2430.141 4.0 6.0 8.0 10.0 1. Using the software package of your choice (e.g., Matlab or Excel), determine CL(i) and Crn1/2 () 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: CL E 10.2,0.4,0.6)