Compressible Flow Calculator

Calculate Mach number, stagnation properties, and area ratios for isentropic compressible gas flow.

Flow Mach number. Subsonic: <1, Supersonic: >1.
Total temperature (at rest).
K
Total pressure (at rest).
kPa
Air: 1.4, Exhaust: 1.3.

Results

Static Temperature-K
Static Pressure-kPa
Density Ratio ρ/ρ0-
Area Ratio A/A*-
Flow Velocity-m/s
References: Anderson — Compressible Flow; Shapiro — Gas Dynamics