) Air is supplied to a converging diverging nozzle from a lage tank where P-2 MPa, T-400k as shown. Anormal shock Wave forms in the diverging Part of the nozzle at a point where Po₁ = b₂ = 2MPa. The upstream mach no. Ma-1.4. The area of the nozzle exit to the throat area is 1.6. Determine. 1. Downstream March no, after the shoele Maz 2. Exit Machno. May. 3. Pressure and temperature at exit, Py and Ty. 0 B-2MPa To=4ook thread Noml shock Wane excit 0.