Normal Shock Calculator
Calculate property changes across a normal shock wave in supersonic flow. Normal shocks occur when supersonic flow encounters an obstruction, resulting in a sudden change in flow properties.
Normal Shock Visualization
Enter a Mach number to see shock details
Normal Shock Theory
What is a Normal Shock Wave?
A normal shock wave is a thin, nearly discontinuous region where flow properties change abruptly. It occurs when:
- Supersonic flow (M₁ > 1) transitions to subsonic flow (M₂ < 1)
- The shock front is perpendicular to the flow direction
- Properties change significantly across a very short distance
Key Normal Shock Properties
- Supersonic flow (M₁ > 1) becomes subsonic (M₂ < 1)
- Static pressure increases (p₂ > p₁)
- Static temperature increases (T₂ > T₁)
- Density increases (ρ₂ > ρ₁)
- Total pressure decreases (p₀₂ < p₀₁) due to entropy generation
- Total temperature remains constant (T₀₂ = T₀₁)
Applications
Supersonic Inlets
Normal shocks occur in supersonic aircraft inlets, slowing airflow to subsonic speeds for the engine.
Wind Tunnels
Used in supersonic wind tunnel design and for experimental measurements of supersonic flow.
Pitot Tubes
Pitot tubes in supersonic flow create normal shocks, allowing Mach number determination from pressure measurements.