You have an airfoil with a span of $18$ inches and chord of $8$ inches, mounted in the wind tunnel at a small angle of attack. You turn on the tunnel and the force balance reads lift of $2\mathrm{.}0$ lbf$.$ The differential pressure meter, which indicates p$$p$\backslash$infty in the tunnel as measured by a pitot$-$static probe, reads $0\mathrm{.}35$ kPa. Assuming that the freestream density, $\backslash$rho $\backslash$infty $,$ is $1\mathrm{.}23$ kg$/$m$^3$

$,$ calculate the section lift coefficient Cl

Choice $1$ of $0\mathrm{.}06$

Choice $2$ of $0\mathrm{.}19$

Choice $3$ of $0\mathrm{.}27$

Choice $4$ of $0\mathrm{.}45$

Choice $5$ of $1\mathrm{.}1$