question 1.d solving using matlab

reference : fundamentals of aerodynamics ch.4 by john d. anderson

Term Project #2 (Due . 11/23 1. Symmetric Airfoil (NACA0012) Fig. 1 NACA 0012 (a) Explain the procedure for the constant-strength vortex panel method in detail. (10pts) (b) Obtain the Cp distribution along the surface (Cp vs. x/c) from -5 to 20 angle of attack (AOA) at intervals of 50 with constant-strength vortex panel method. (10pts) (c) Explain how you evaluate the C from the Cp distribution. (10pts) (d) Plot the C versus AOA. (10pts) (e) Compare the result of (d) with that from thin airfoil theory and experiments and discuss the limitation of the panel methods. (10pts)