Air enters a converging-diverging nozzle at a stagnation pressure of 2mpa, a stagnation temperature of 400k, and a mach number of 0.5. the flow is accelerated isentropically through the nozzle to a mach number of 4(station x), passes through a normal shock (x to y), and then flows isentropically to the exit. given a nozzlethroat area of 0.05m2 and exit area of 1m2, find the location of the shock (nozzle area).