$5\mathrm{.}3$ Consider a rectangular wing mounted in a low$-$speed subsonic wing tunnel. The wing model completely spans the test section so that the flow "sees" essentially an infinite wing. If the wing has an NACA $23012$ airfoil section and a chord of $0\mathrm{.}3$ m $,$ calculate the lift, drag, and moment about the quarter$-$chord per unit span when the airflow pressure, temperature, and velocity are $1$atm,$303K,$ and $42\frac{m}{s},$ respectively. The angle of attack is $8.$

$5\mathrm{.}4$ The wing model in Prob. $5\mathrm{.}3$ is pitched to a new angle of attack, where the lift on the entire wing is measured as $200$ N by the wind tunnel force balance. If the wingspan is $2$ m $,$ what is the angle of attack?