Normal Shock Wave 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 initially assumed to be ideal, non-reacting .
Upstream Mach Number (M1)
Ratio of Specific Heats (γ)


Downstream Mach Number (M2)

Static pressure ratio (P2/P1)

Static temperature ratio (T2/T1)

Total pressure ratio (PO2/PO1)