a convergent-divergent nozzle with an exit-to-throat area ratio of 1.616 has exit and reservoir pressures equal to 0.947 an 1.0 atm, respectively. in addition, the reservoir temperature is 288 k and the throat area is 0.3 m2. assuming isentropic flow through the nozzle, calculate the mach number, pressure, and mass flow rate at the throat. 4- (20 pts) consider the flow through a convergent-divergent duct with an exit-to-throat area ratio of 2. the reservoir pressure is 1 atm, and the exit pressure is 0.95 atm calculate the mach numbers at the throat and at the exit. 5 - (20 pts) consider a convergent-divergent nozzle with an exit-to-throat area ratio of 3. a normal shock wave is inside the divergent portion at a location where the local area ratio is a/a, = 2, calculate the exit-to-reservoir pressure ratio.