Point-Vortex Panel Method In this problem, you will implement a point-vortex panel method for a symmetric thin airfoil, and compare the results of it to theory. Consider a unit-chord (c = 1), zero thickness, zero camber airfoil. Write a Matlab code that: a) reads in a value of N; ranging b) breaks the camber line into N panels, using cosine spacing (i.e. divide the line from 0 to into N evenly spaced panels (N + 1 points), and calculate the x values from x/c = 1/2(1 cos 0)); c) places a point vortex 1/4 of the way along each panel, and a collocation point 3/4 of the way along each panel; d) sets up the influence coefficient matrix for this setup; e) reads in a value of a f) sets up the r vector for this (take V = 1) g) solves the system for the vortex strengths; h) plots F(x) from your method and compares it to the distribution we got from thin airfoil theory, i.e. F(x) = 2a1 c-x dx Run your code for N = 10 and N x = 100, with a = 5 and a = 10.