Question: A convergent-divergent nozzle through which air flows is designed to generate Mach 2.2. The supply reservoir pressure is 2.2 MPa and the flow is discharged into ambient air at a pressure of 101 kPa. Under these conditions, the nozzle will be underexpanded, and as a result, expansion waves will exist at the nozzle exit. Find the flow direction just downstream of the exit plane expansion waves under these conditions. What effect does the presence of the expansion waves have on the net axial thrust produced by the nozzle?