Isentropic Flow Calculator
Calculate thermodynamic properties across an isentropic flow. Isentropic flow is a flow process where entropy remains constant, which occurs in ideal compressible flow with no heat transfer or friction.
Isentropic Flow Results:
Mach Number
2.000
Supersonic flow
Area Ratio
1.688
A/A* (ratio to sonic throat)
Pressure Ratio
0.1278
p/p₀ (static to stagnation)
Temperature Ratio
0.5556
T/T₀ (static to stagnation)
Density Ratio
0.2300
ρ/ρ₀ (static to stagnation)
Pitot Pressure Ratio
5.6404
p₀₂/p₀ (for supersonic with shock)
Mach Angle
30.00°
μ = sin⁻¹(1/M) - Angle of Mach wave
Prandtl-Meyer Angle
26.38°
ν - Maximum turning angle for isentropic expansion
Specific Heat Ratio (γ)
1.400
Gas: Air
Open Source and Easy to Use Elsewhere
This tool is open source and the underlying logic is fully transparent. You can inspect the code, understand the calculations, and contribute improvements. If you want to use the tool in your own website, course page, or learning platform, you can also embed it directly and start from a ready-made iframe setup for this exact tool.
Open source: review the implementation and see how the results are produced.
Embeddable: preview this tool, copy the iframe, and use it in your own site or LMS.