Consider a rocket engine burning hydrogen and oxygen. The combustion chamber temperature and pressure are \(4000 \mathrm{~K}\) and \(15 \mathrm{~atm}\), respectively. The exit pressure is \(1.174 \times 10^{-2} \mathrm{~atm}\). Calculate the Mach number at the exit. Assume that \(\gamma=\) constant \(=1.22\) and that \(R=519.6 \mathrm{~J} / \mathrm{kg} \mathrm{K}\).