Soren Sabet Sarvestany

     For an aerodynamics assignment question (#1), I was tasked with solving for the lift slope and the induced drag coefficient. We were instructed to model the airfoil as a thin plate, and were given the aspect ratio, as well as the ratio of the cord between the center of the span and the wing tips. 

     To solve, I wrote a script in MATLAB which can be found here. Since the lift distribution was symmetric, I modeled it using only the odd terms in the series expansion for thin airfoil theory. I used angles varying between pi/8 and pi/2 to create a system of 7 equations with 7 unknowns. By taking the inverse of this matrix, I was able to solve for the first seven odd coefficients, thereby giving me the lift and the induced drag coefficient.