(25 points). Consider a rocket nozzle fed by a combustion chamber as shown in the figure below. The temperature and pressure in the combustion chamber (reservoir) are 3000 K and 10 MPa, respectively. R = 461.5 J/kg K; y = 1.33. Assume the flow to be isentropic. Station 2 is the throat, assume the flow is sonic there. Station 3 is the nozzle exit plane. Assume the flow velocity at the exit plane is 3000 m/s. Fill out the table below. Station 1 Station 2 Station 3 To = 3000K Po = 10MPa sonic v = 3000 m/s Station 2 Station 1 Reservoir Station 3 10 MPa To P T P* T* V M M* 3000 K