In a supersonic nozzle flow, the exit-to-throat area ratio is \(10, p_{o}=10.00 \mathrm{~atm}\), and the backpressure \(p_{B}=0.04 \mathrm{~atm}\). Calculate the angle \(\theta\) through which the flow is deflected immediately after leaving the edge (or lip) of the nozzle exit.