$1.$ Consider the graphs shown for the NACA $4416$ airfoil with and without a $30$ deg. deflection of a trailing$-$edge flap.Assume that the flow is at a Reynolds number of $8\mathrm{.}2$ million and standard sea level conditions. a$.$ What is for a flap deflection of $0?$ b$.$ What is for a flap deflection of $30?$ c$.$ If this airfoil were flying at $100$ mph and its chord is $6$ feet long, how much more lift per unit span, in pounds, do you obtain when you deflect the flap? d$.$ How much more pitching moment? e$.$ In the situation of question d$,$ how much force would you have to generate on a horizontal tail to cancel the pitching moment caused by the deflection of the flap, assuming that this surface is located $20$ feet behind the wing? Is this force upwards, or downwards?$2.$ Consider the following wing: Assume that, due to its shape, it has an Oswald efficiency of $0\mathrm{.}88.$ The wing features a NACA $4416$ airfoil without flaps. What is the induced drag coefficient of this wing if it is operating at an angle of attack of $6$ degrees?