Consider the isentropic flow over an airfoil. The free stream conditions correspond to a standard altitude of 10,000 ft and M∞ = 0.82. At a given point on the airfoil, M = 1.0. Calculate p and T at this point. (Note: You will have to consult a standard atmosphere table for this problem, such as given in Ref. 2. If you do not have one, you can find such tables in any good technical library.)