Calculate stagnation properties for compressible gas flow based on Mach number.
Flow Parameters
Calculation Results
Enter Mach number and Gamma to calculate
Quick Reference
MMach Number
T₀, P₀, ρ₀Stagnation properties
T, P, ρStatic properties
A/A*Area ratio for sonic throat
Overview
Isentropic flow is a flow that is both adiabatic and reversible. In gas dynamics, these relations describe how pressure, temperature, and density change as a gas accelerates or decelerates, assuming no heat transfer or friction losses.
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Pro Tips
Mach 1 is the speed of sound.
For air, γ is typically 1.4.
Stagnation (Total) properties are the values the gas would have if it were brought to rest isentropically.
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Fun Facts
"Compressibility effects usually become important above Mach 0.3."
"The 'stagnation point' on the leading edge of a wing is where the flow is brought to zero velocity."
"These equations are vital for designing supersonic jets and rocket nozzles."
