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 .
Inputs
Upstream Mach Number (M1)
Ratio of Specific Heats (γ)

 


Results
Downstream Mach Number (M2)

 
Static pressure ratio (P2/P1)

 
Static temperature ratio (T2/T1)

 
Total pressure ratio (PO2/PO1)