A supersonic wind tunnel test section is designed to have \(M=2.5\) at \(15^{\circ} \mathrm{C}\) and \(35 \mathrm{kPa}\) absolute. The fluid is air. Determine the required inlet stagnation conditions, \(T_{0}\) and \(p_{0}\). Calculate the required mass flow rate for a test section area of \(0.175 \mathrm{~m}^{2}\).