A supersonic airflow at Ma1 = 3.2 and p1 = 50 kPa undergoes a compression shock followed

Question:

A supersonic airflow at Ma1 = 3.2 and p1 = 50 kPa undergoes a compression shock followed by an isentropic expansion turn. The flow deflection is 30° for each turn. Compute Ma2 and p2 if
(a) The shock is followed by the expansion and
(b) The expansion is followed by the shock.