Supersonic Flow over a wedge and cone M-3 Air flowing with a Mach number of 3, a pressure of 1 atm and a temperature of 300K passed over a 15 angle wedge leads to the generation of an oblique shock wave. 15 1. Determine Mach number behind the shock M and pressure coefficient Cp Where Shock wave angle can be found from deflection angle 0. Upstream Mach number perpendicular to the shock (Mn1): Mn1 = M sin . Mach number behind the shock can be found from M = M2/ sin (-0) Pressure Coefficient (Cp) can be found from: C=(2 y M2)(p2/p - 1),