Consider a convergent-divergent duct with exit and throat areas of \(0.50 \mathrm{~m}^{2}\) and \(0.25 \mathrm{~m}^{2}\), respectively. The inlet reservoir pressure is \(1.0 \mathrm{~atm}\) and the exit static pressure is \(0.6 \mathrm{~atm}\). For this pressure ratio, the flow will be supersonic in a portion of the nozzle, terminating with a normal shock inside the nozzle. Calculate the local area ratio \(\left(A / A^{*}\right)\) at which the shock is located inside the nozzle.