For a 2D airfoil with chord c the following characteristics are foundby wind tunnel experiments (where the angle of attack a is indegrees): C₁ = 0.121-a + 0.125 CmTE0=.0915 = + 0.075 Drag can be neglected. When answering problems b), c) and d), be sure to add a clear sketch of the situation. a.What can be concluded about the camber of the airfoil? Explain your answer. Calculate the location of the center of pressure XCP/Cfor alpha = 0°. Calculate the location of the center of pressure XCP/Cfor alpha = 5°. Calculate the location of the aerodynamic center XAC/C