1. Design a typical section (airfoil) for your airplane based on the normal Mach number, effective Cl, and normal t/c. Use the program PANDA and apply the following constraints:
Print out a plot of the airfoil and pressure distribution. Those designing supersonic aircraft, should do this problem as an exercise unrelated to their sections (Use Cl = 0.7 M= 0.7 t/c = 0.12).
2. Evaluate the airfoil using the nonlinear transonic code described in class; show the pressure distribution and compare with the subsonic results. Additional information on this problem is available by clicking on this link.
Please remember to describe the approach to your design and analysis tasks clearly. Printouts of results without a discussion of how you got to that point are not acceptable.