Problem 1 (20%)
Starting with Equations (1.7), (1.8), and (1.11)
N^(')=-\int_(LE)^(TE) (p_(u)cos\theta \tau _(u)sin\theta )ds_(u) \int_(LE)^(TE) (p_(l)cos\theta -\tau _(l)sin\theta )ds_(l)
A^(')=\int_(LE)^(TE) (-p_(u)sin\theta \tau _(u)cos\theta )ds_(u) \int_(LE)^(TE) (p_(l)sin\theta \tau _(l)cos\theta )ds_(l)
M_(LE)^(')=\int_(LE)^(TE) [(p_(u)cos\theta \tau _(u)sin\theta )x-(p_(u)sin\theta -\tau _(u)cos\theta )y]ds_(u)
\int_(LE)^(TE) [(-p_(l)cos\theta \tau _(l)sin\theta )x (p_(l)sin\theta \tau _(l)cos\theta )y]ds_(l)
, derive aerodynamic coefficients in detail Equations (1.15), (1.16), and (1.17).