Normal Shock Calculations   This form calculates properties of air flow through a normal shock wave. The required input is the Mach number of the upstream flow. The gas is assumed to be ideal air.   Tabulated Data
Inputs Upstream Mach Number (M1)	Results Downstream Mach Number (M2)   Static pressure ratio (P2/P1)   Static temperature ratio (T2/T1)   Total pressure ratio (Po2/Po1)

(c) 2006 AMME, University of Sydney.