A wing model of \(5 \mathrm{in}\). chord and \(2.5 \mathrm{ft}\) span is tested at a certain angle of attack in a wind tunnel at \(60 \mathrm{mph}\) using air at \(14.5 \mathrm{psia}\) and \(70^{\circ} \mathrm{F}\). The lift and drag are found to be \(6.0 \mathrm{lbf}\) and \(0.4 \mathrm{lbf}\) respectively. Calculate the lift and drag coefficient for the model at this angle of attack.