Question: Consider a rocket engine that burns hydrogen and oxygen. The combustion chamber temperature and pressure are 3800 K and 1.5 MPa, respectively, the velocity in the combustion chamber being very low. The pressure on the nozzle exit plane is 1.5 kPa. Assuming that the flow is isentropic, find the Mach number and the velocity on the exit plane. Assume that the products of combustion behave as a perfect gas with γ = 1.22 and R = 519.6 J/kg K.