$(20$ pts$)$ Your wind tunnel measurements using an aerodynamic balance report a section lift of

$13\mathrm{.}7($lb$)/($ft$),$ a section drag of $0\mathrm{.}114($lb$)/($ft$),$ and a section pitching moment of $-0\mathrm{.}456($l$*$ft$)/($ft$)$ about the

quarter chord location. Determine the section coefficients for normal force, section axial force;

section pitching moment about the leading edge, and the center of pressure location. The wing

had a chord length of $16$ inches and was at an angle of attack of $4\backslash$deg $.$ The test section had a velocity

of $(120^($ft$))/(\_($S$))$ and was at standard sea$-$level conditions $($p$=2116$psf$,$T$=519\backslash$deg R$)$