You are asked to design the wing of a glider which will perform a steady unpowered flight, as shown in Figure 1 The goal is to maximize the range that it can fly (i.e. R in the figure) for a given altitude H. You can choose an airfoil section from a given list: NACA 0012, NACA 2412, NACA 4412, and Clark Y. Which airfoil do you choose and why? Support your answer by equations. What should be the angle of attack of the glider in order to maximize R. You can use the information given on http://www.airfoiltools.com/. Assume that the Reynolds number is Re = 106. Hint: Draw the free-body diagram for the glider. Figure 1: An aircraft performing a steady gliding flight (Anderson1999: Aircraft Performance and Design).