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.