The figure indicates a hypothetical one-dimensional supersonic inlet installed in a wind t...

The figure indicates a hypothetical one-dimensional supersonic inlet installed in a wind tunnel and equipped with a throttle valve by which the downstream static pressure p2 might be varied. Suppose that the inlet is designed for a Mach number M = 3.0 and that with this flight Mach number the shock has been swallowed and an internal shock exists, as at  Neglecting all losses except those occurring in the shock, calculate and plot the shock Mach number Ms and the stagnation pressure ratio p02/p0a as a function of the static pressure ratio p2/pa (for γ = 1.4). Let p2/pa range from unity to well beyond that value which disgorges the shock