At a given point in a supersonic wind tunnel, the pressure and temperature are \(5 \times 10^{4} \mathrm{~N} / \mathrm{m}^{2}\) and \(200 \mathrm{~K}\), respectively. The total pressure at this point is \(1.5 \times 10^{6} \mathrm{~N} / \mathrm{m}^{2}\). Calculate the local Mach number and total temperature.