Question $1(2$ parts a$,$ b$)$:

Two rectangular wings are made for a test in a wind tunnel at $0$ angle of attack. One wing has a NACA $0000$ cross section, and the other is composed of a NACA $2412.$ The flow conditions are such that the Reynolds Number per meter $($i$.$e$.\frac{V}{})$ is $1\mathrm{.}2{10}^6{m}^{-1}.$ You may ignore compressibility effects and assume that boundary layer flow transition occurs at a critical Reynolds Number of $500,000.$

a$.$ For the two $3$D wings, assuming they have the same chord & span, which wing has greater: pressure drag, skin friction drag, & induced drag? Explain your reasoning. $($You don't need to calculate anything$).$

b$.$ ou insert the NACA $2412$ wing within a cylindrical fuselage to create an aircraft model such that $10\%$ of the wing area is imbedded within the fuselage. Determine the profile drag coefficient $C_{D,P}$ of the wing of this aircraft if the chord length is $0\mathrm{.}2$ m $.$ You may consult Fig. $11\mathrm{.}3$ in your estimation.