Consider a 20 Degree half-angle wedge in a supersonic flow at Mach 3.0 at standard sea-level conditions

Q. Consider a 20⁰ half-angle wedge in a supersonic flow at Mach 3.0 at standard sea-level conditions. If the shock-wave angle on the wedge is 36⁰, the Mach number of the tangential component of the flow post-shock is  (accurate to two decimal places).

Ans: 47.0 to 55.0