$\backslash (!\backslash )$

Required Information

Consider a positively cambered airfoil with a zero$-$lift angle of $\backslash (-4\mathrm{.}000^\{\backslash$circ$\}\backslash ).$ The lift slope is $0\mathrm{.}1$ per degree.

Now imagine the same airfoil turned upside$-$down, but at the same $\backslash (5^\{\backslash$circ$\}\backslash )$ angle of attack as part $($a$).$ Calculate the lift coefficient. $($Round the final answer to one decimal place.$)$

The lift coefficient is