c$\_($m$\_($m$\_($u$)))=(\backslash$pi $)/(2)($A$\_(0)+$A$\_(1)-($A$\_(1))/(4))$ For the NACA $2412$ alfoil, the lift coefficlent and moment coefficlent about the quarter$-$chord at $\backslash (-6^\{\backslash$circ$\}\backslash )$ angle of attack are $-0\mathrm{.}39$ and $-0\mathrm{.}045,$ respectively. At $\backslash (4^\{2\}\backslash )$ angle of attack, these coefficlents are $0\mathrm{.}65$ and $-0\mathrm{.}037,$ respectlvely. Calculate the location of the aerodynamic center. $($Round the final answer to three decimal places.$)$

The location of the aerodynamic center is