Isentropic Stagnation Pressure Calculator
Reviewed by Hamza Gujjar, Algorithm Architect & Software Developer
Last updated: July 26, 2026Isentropic Stagnation Pressure Calculator
At high flow speeds, static pressure and stagnation (total) pressure diverge substantially - this calculator finds that stagnation pressure from static pressure and Mach number.
The Formula
P0 = P × (1 + ((γ-1)/2) × M²)γ/(γ-1)
Worked Example
Static pressure 101.325 kPa at Mach 2 in air (γ=1.4): P0 ≈ 792.8 kPa - nearly 8 times the static pressure, matching standard compressible flow reference tables.
How to Use This Calculator
- Enter static pressure.
- Enter Mach number.
- Enter the gas's specific heat ratio (1.4 for air).
This gap between static and stagnation pressure is exactly why high-speed flow instrumentation and design (like supersonic inlet design) must carefully distinguish between the two rather than treating pressure as a single number.