A rocket nozzle has an exit-to-throat area ratio of 4.0. The exhaust gases are generated in a combustion chamber with stagnation pressure equal to 4 MPa and stagnation temperature equal to 2000 K. Assume the working fluid to behave as a perfect gas with k = 1.3 and molar mass = 20 kg/kmol. Determine
(a) The rocket exhaust velocity and
(b) The mass flow rate. Assume isentropic steady flow except at the nozzle exit where a normal shock is located as shown in the accompanying figure.