For the inlet conditions of problem 3.9, calculate the maximum fuel-air ratio beyond which the flow will be choked at the exit.

Data from problem 3.9

Air enters the combustor of a jet engine at \(p_{1}=10 \mathrm{~atm}, T_{1}=1000^{\circ} \mathrm{R}\), and \(M_{1}=0.2\). Fuel is injected and burned, with a fuel-air ratio (by mass) of 0.06 . The heat released during the combustion is \(4.5 \times 10^{8} \mathrm{ft}-\mathrm{lb}\) per slug of fuel. Assuming one-dimensional frictionless flow with \(\gamma=1.4\) for the fuel-air mixture, calculate \(M_{2}, p_{2}\), and \(T_{2}\) at the exit of the combustor.