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)

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