$1-$ Considering the wing section below, explain how there is lift at zero AOA

$2-$ Estimate the absolute pressure peak on the airfoil on an aircraft at landing speed EAS $($Equivalent Air Speed$)$ of $110$

$kn$ at sea level. Assume: air density $1\mathrm{.}225k\frac{g}{m^{{?}^{{?}^{?}}}}3,$ ambient pressure $101\mathrm{.}34$kPa,AOA$=8^0.$ Use approximations on

the plot below.