(Solved): Consider three wing designs: 1. A rectangular wing, such as on Pilatus PC-6 Turbo Porter (see figur ...

Consider three wing designs: 1. A rectangular wing, such as on Pilatus PC-6 Turbo Porter (see figure) 2. A tapered trapezoidal wing, with a taper ration of $?=0.30$, such as on Cessna Citation Bravo (see figure). 3. An elliptic wing, such as on the legendary World War II Supermarine Spitfire (see figure). Assume each is constructed from a single cambered airfoil with the following characteristics: 1. Twist: linear twist, with a total twist of ${?}_T=?3^{?}$. 2. Section lift-curve slope $C_{l?}=2?(0.96)/$ radian 3. Semi-span length $b/2=1$ 4. Aspect ratio $\mathrm{A}=8$ 5. Wing absolute AOA at center section ${?}_0=5^{?}$. A. Develop a computer program that uses numerical lifting-line theory to calculate the following aerodynamic characteristics for these wings. 1. Total wing lift coefficient $C_L$ 2. Total wing induced drag coefficient $C_{Di}$ 3. Spanwise lift distribution normalized with total wing lift coefficient $C_l(y)/C_L$ 4. Spanwise distribution of bound circulation $?(y)$ 5. $?=\left(?A{C}_{Di}/C_L^2\right)?1$ B. Use cosine spacing for the trailing vortex locations. Control point locations will be half way between neighboring trailing vortices. Compute your results for $n=2,8$, 32 , and 128 . To save paper, give only one table for the right half of all three wings for $\mathrm{n}=128$, presenting the three cases side by side, in the form: Generate three other small tables on one page to summarize your overall results one for each of the three wings for all $n$ values used, in the form: