Consider a C-D nozzle connected to a large tank of air where the tank pressure is 600kPa and the tank temperature is 40°C.
a. Under ideally expanded conditions the exit pressure is 100 kPa; what is the Mach number and the velocity at the exit?
b. If the nozzle minimum area is 2 cm^2, what is the area at the exit?
c. What is the total thrust produced by the nozzle under these conditions?
d. What is the back pressure for a normal shock to occur at the nozzle exit plane?
e. At certain back pressures, the flow is subsonic everywhere in the nozzle except at the throat. What is the thrust produced by the nozzle under these conditions?