The minimum $C_p$ on the upper surface of certain airfoil is $-1\mathrm{.}05.$ If the freestream is at $99f\frac{t}{s},$

what is the velocity of the flow at that point on the upper surface?

What is the pressure at that point? Assume that the chord is $1ft$ and that the freestream is at

standard sea level conditions.

If the airfoil generates a lift coefficient of $0\mathrm{.}7,$ what value of circulation $$ would correspond to

it$?$

What is the location in polar coordinates of the stagnation point$($s$)$ of a three$-$inch diameter

spinning cylinder that can generate the same $c_l$ due to the Magnus effect?

What is the location of the lowest pressure coefficient on the cylinder's surface?

What is that value of the coefficient?

What is the highest pressure coefficient on the surface of the cylinder?