Q$2/$ Shock Reflections in an Over Expanded Nozzle. A supersonic stream leaves a nozzle in parallel flow

$($Region a$)$ at Mach $2\mathrm{.}0$ and a pressure of $10$ psia $.$ The pressure of the atmosphere into which the jet flow

discharges is $15$ psia $.$

Take $1$ bar$=14\mathrm{.}7$ psia.

$($a$)$ Calculate the pressure in Region b

$($b$)$ Calculate the pressure in Region c

$($c$)$ Determine the inclination angles of the free boundary interface $($dashed line$)$

$($d$)$ Make a scale drawing of the streamline and shock pattern, clearly indicating all of the angles.