Consider a flat plate mounted in the test section of a supersonic wind tunnel. The plate is at an angle of attack of \(10^{\circ}\) and the static pressure on the top surface of the plate is \(1.0 \mathrm{~atm}\). The nozzle throat area is \(0.0500 \mathrm{~m}^{2}\) and the exit area is \(0.0844 \mathrm{~m}^{2}\). Calculate the reservoir pressure of the tunnel.