3. 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 p: 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 num- ber M, and the stagnation pressure ratio Puz/pa. as a function of the static pressure ratio p/p. (for y=1.4). Let p/p. range from unity to well beyond that value which disgorges the shock.