Normal shocks in perfect gases

Normal Shock Wave Relations - Advanced Compressible Flow Calculations

Input Parameters
Enter the upstream Mach number to calculate all normal shock properties

Mach number must be greater than 1 for normal shock waves

Default value: 1.3 (typical for air at high temperatures)

Normal Shock Results
All calculated properties across the normal shock wave

Enter upstream Mach number (Mₓ > 1) and click Calculate to see normal shock results