Consider a flat plate at an angle of attack of \(4^{\circ}\).

a. Calculate \(C_{L}\) and \(C_{M_{c / 4}}\) for \(M_{\infty}=0.03\) (essentially incompressible flow). (Hint: Consult a book, such as Ref. 104, for the aerodynamic properties of a flat plate using incompressible flow thin airfoil theory.)

b. Apply the Prandtl-Glauert rule to the results of part (a), and calculate \(C_{L}\) and \(C_{M_{c / 4}}\) for \(M_{\infty}=0.6\).