In a supersonic wind tunnel utilizing air similar to that shown in given Figure, the converging-diverging nozzle section has an inlet isentropic stagnation pressure of 3.20 atm.
The test section has a Mach number of 2.70, and the convergingdiverging diffuser section has an exit pressure of 1.00 atm. Determine the efficiency of the converging-diverging diffuser section.
